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

NASA Technical Reports Server (NTRS)

Eubanks, ED; Gibb, John

1990-01-01

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

In-Orbit Collision Analysis for VEGA Second Flight

NASA Astrophysics Data System (ADS)

Volpi, M.; Fossati, T.; Battie, F.

2013-08-01

ELV, as prime contractor of the VEGA launcher, which operates in the protected LEO zone (up to 2000 km altitude), has to demonstrate that it abides by ESA debris mitigation rules, as well as by those imposed by the French Law on Space Operations (LOS). After the full success of VEGA qualification flight, the second flight(VV02) will extend the qualification domain of the launcher to multi-payload missions, with the release of two satellites (Proba-V and VNRedSat-1) and one Cubesat (ESTCube-1) on different SSO orbits The multi-payload adapter, VESPA, also separates its upper part before the second payload release. This paper will present the results of the long-term analyses on inorbit collision between these different bodies. Typical duration of propagation requested by ELV customer is around 50 orbits, requiring a state-of-the-art simulator able to compute efficiently orbits disturbs, usually neglected in launcher trajectory optimization itself. To address the issue of in-orbit collision, ELV has therefore developed its own simulator, POLPO [1], a FORTRAN code which performs the long-term propagation of the released objects trajectories and computes the mutual distance between them. The first part of the paper shall introduce the simulator itself, explaining the computation method chosen and briefly discussing the perturbing effects and their models taken into account in the tool, namely: - gravity field modeling (zonal and tesseral harmonics) - atmospheric model - solar pressure - third-body interaction A second part will describe the application of the in-orbit collision analysis to the second flight mission. Main characteristics of the second flight will be introduced, as well as the dispersions considered for the Monte-Carlo analysis performed. The results of the long-term collision analysis between all the separated bodies will then be presented and discussed.

Heavy Lift Launch Capability with a New Hydrocarbon Engine

NASA Technical Reports Server (NTRS)

Threet, Grady E., Jr.; Holt, James B.; Philips, Alan D.; Garcia, Jessica A.

2011-01-01

The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center was tasked to define the thrust requirement of a new liquid oxygen rich staged combustion cycle hydrocarbon engine that could be utilized in a launch vehicle to meet NASA s future heavy lift needs. Launch vehicle concepts were sized using this engine for different heavy lift payload classes. Engine out capabilities for one of the heavy lift configurations were also analyzed for increased reliability that may be desired for high value payloads or crewed missions. The applicability for this engine in vehicle concepts to meet military and commercial class payloads comparable to current ELV capability was also evaluated.

Project ELaNa and NASA's CubeSat Initiative

NASA Technical Reports Server (NTRS)

Skrobot, Garrett Lee

2010-01-01

This slide presentation reviews the NASA program to use expendable lift vehicles (ELVs) to launch nanosatellites for the purpose of enhancing educational research. The Education Launch of Nanosatellite (ELaNa) project, run out of the Launch Services Program is requesting proposals for CubeSat type payload to provide information that will aid or verify NASA Projects designs while providing higher educational research

Transportation systems analyses. Volume 2: Technical/programmatics

NASA Astrophysics Data System (ADS)

1993-05-01

The principal objective of this study is to accomplish a systems engineering assessment of the nation's space transportation infrastructure. This analysis addresses the necessary elements to perform man delivery and return, cargo transfer, cargo delivery, payload servicing, and the exploration of the Moon and Mars. Specific elements analyzed, but not limited to, include the Space Exploration Initiative (SEI), the National Launch System (NLS), the current expendable launch vehicle (ELV) fleet, ground facilities, the Space Station Freedom (SSF), and other civil, military and commercial payloads. The performance of this study entails maintaining a broad perspective on the large number of transportation elements that could potentially comprise the U.S. space infrastructure over the next several decades. To perform this systems evaluation, top-level trade studies are conducted to enhance our understanding of the relationships between elements of the infrastructure. This broad 'infrastructure-level perspective' permits the identification of preferred infrastructures. Sensitivity analyses are performed to assure the credibility and usefulness of study results. This report documents the three principal transportation systems analyses (TSA) efforts during the period 7 November 92 - 6 May 93. The analyses are as follows: Mixed-Fleet (STS/ELV) strategies for SSF resupply; Transportation Systems Data Book - overview; and Operations Cost Model - overview/introduction.

GEOTAIL Spacecraft historical data report

NASA Technical Reports Server (NTRS)

Boersig, George R.; Kruse, Lawrence F.

1993-01-01

The purpose of this GEOTAIL Historical Report is to document ground processing operations information gathered on the GEOTAIL mission during processing activities at the Cape Canaveral Air Force Station (CCAFS). It is hoped that this report may aid management analysis, improve integration processing and forecasting of processing trends, and reduce real-time schedule changes. The GEOTAIL payload is the third Delta 2 Expendable Launch Vehicle (ELV) mission to document historical data. Comparisons of planned versus as-run schedule information are displayed. Information will generally fall into the following categories: (1) payload stay times (payload processing facility/hazardous processing facility/launch complex-17A); (2) payload processing times (planned, actual); (3) schedule delays; (4) integrated test times (experiments/launch vehicle); (5) unique customer support requirements; (6) modifications performed at facilities; (7) other appropriate information (Appendices A & B); and (8) lessons learned (reference Appendix C).

Commercial Titan ELV - Filling a need in the national Space Transportation System

NASA Astrophysics Data System (ADS)

Jenkins, T. M.; Davis, R. M., Jr.

1983-06-01

The design and performance capabilities of the Titan 34D launch vehicle are reviewed, noting that it is proven launch system that is capable of complementing the Shuttle in terms of having an available, large payload-capacity launch system for domestic satellites. The Titan's development began in the 1950s as an ICBM, and the Titan III configuration was first flown in 1966, followed by 121 operational launches with a 99 percent success rate. The current configuration features a fairing large enough to hold a 150 in. diam payload. Satellites up to 12,500 lb can be launched into GEO, 27,600 lb into polar orbits, and 34,100 lb into LEO. The Titan 34D is reconfigurable and can carry payloads that would otherwise be handled by the Shuttle.

Electromagnetic Compatibility Analysis Group VA-H3

NASA Technical Reports Server (NTRS)

Armanda, Carlos A.

2008-01-01

During the eight weeks working at NASA, I was fortunate enough to work with the Expendable Launch Vehicle's (ELV) Electromagnetic Compatibility (EMC) Team, who is responsible for the evaluation and analysis of any EMI risk an ELV mission might face. This group of people concern themselves with practically any form of electromagnetic interference that may risk the safety of a rocket, a mission, or even people. Taking this into consideration, the group investigates natural forms of interference, such as lightning, to manmade interferences, such as antennas.

Probability of Failure Analysis Standards and Guidelines for Expendable Launch Vehicles

NASA Astrophysics Data System (ADS)

Wilde, Paul D.; Morse, Elisabeth L.; Rosati, Paul; Cather, Corey

2013-09-01

Recognizing the central importance of probability of failure estimates to ensuring public safety for launches, the Federal Aviation Administration (FAA), Office of Commercial Space Transportation (AST), the National Aeronautics and Space Administration (NASA), and U.S. Air Force (USAF), through the Common Standards Working Group (CSWG), developed a guide for conducting valid probability of failure (POF) analyses for expendable launch vehicles (ELV), with an emphasis on POF analysis for new ELVs. A probability of failure analysis for an ELV produces estimates of the likelihood of occurrence of potentially hazardous events, which are critical inputs to launch risk analysis of debris, toxic, or explosive hazards. This guide is intended to document a framework for POF analyses commonly accepted in the US, and should be useful to anyone who performs or evaluates launch risk analyses for new ELVs. The CSWG guidelines provide performance standards and definitions of key terms, and are being revised to address allocation to flight times and vehicle response modes. The POF performance standard allows a launch operator to employ alternative, potentially innovative methodologies so long as the results satisfy the performance standard. Current POF analysis practice at US ranges includes multiple methodologies described in the guidelines as accepted methods, but not necessarily the only methods available to demonstrate compliance with the performance standard. The guidelines include illustrative examples for each POF analysis method, which are intended to illustrate an acceptable level of fidelity for ELV POF analyses used to ensure public safety. The focus is on providing guiding principles rather than "recipe lists." Independent reviews of these guidelines were performed to assess their logic, completeness, accuracy, self- consistency, consistency with risk analysis practices, use of available information, and ease of applicability. The independent reviews confirmed the general validity of the performance standard approach and suggested potential updates to improve the accuracy each of the example methods, especially to address reliability growth.

Abnormalities in arterial-ventricular coupling in older healthy persons are attenuated by sodium nitroprusside

PubMed Central

Chantler, Paul D.; Nussbacher, Amit; Gerstenblith, Gary; Schulman, Steven P.; Becker, Lewis C.; Ferrucci, Luigi; Fleg, Jerome L.; Najjar, Samer S.

2011-01-01

The coupling between arterial elastance (EA; net afterload) and left ventricular elastance (ELV; pump performance), known as EA/ELV, is a key determinant of cardiovascular performance and shifts during exercise due to a greater increase in ELV versus EA. This normal exercise-induced reduction in EA/ELV decreases with advancing age. We hypothesized that sodium nitroprusside (SNP) can acutely ameliorate the age-associated deficits in EA/ELV. At rest and during graded exercise to exhaustion, EA was characterized as end-systolic pressure/stroke volume and ELV as end-systolic pressure/end-systolic volume. Resting EA/ELV did not differ between old (70 ± 8 yr, n = 15) and young (30 ± 5 yr, n = 17) subjects because of a tandem increase in EA and ELV in older subjects. During peak exercise, a blunted increase in ELV in old (7.8 ± 3.1 mmHg/ml) versus young (11.4 ± 6.5 mmHg/ml) subjects blunted the normal exercise-induced decline in EA/ELV in old (0.25 ± 0.11) versus young (0.16 ± 0.05) subjects. SNP administration to older subjects lowered resting EA/ELV by 31% via a reduction in EA (10%) and an increase in ELV (47%) and lowered peak exercise EA/ELV (36%) via an increase in ELV (68%) without a change in EA. Importantly, SNP attenuated the age-associated deficits in EA/ELV and ELV during exercise, and at peak exercise EA/ELV in older subjects on drug administration did not differ from young subjects without drug administration. In conclusion, some age-associated deficiencies in EA/ELV, EA, and ELV, in older subjects can be acutely abolished by SNP infusion. This is relevant to common conditions in older subjects associated with a significant impairment of exercise performance such as frailty or heart failure with preserved ejection fraction. PMID:21378146

76 FR 33139 - Launch Safety: Lightning Criteria for Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-06-08

... availability and implement changes already adopted by the United States Air Force. DATES: Effective July 25... identify the docket and amendment numbers of this rulemaking. I. Background On August 25, 2006, the FAA... lightning during flight. Licensing and Safety Requirements for Launch, 71 FR 50508 (Aug. 25, 2006). An ELV...

Characteristics of VLF/LF Sferics from Elve-producing Lightning Discharges

NASA Astrophysics Data System (ADS)

Blaes, P.; Zoghzoghy, F. G.; Marshall, R. A.

2013-12-01

Lightning return strokes radiate an electromagnetic pulse (EMP) which interacts with the D-region ionosphere; the largest EMPs produce new ionization, heating, and optical emissions known as elves. Elves are at least six times more common than sprites and other transient luminous events. Though the probability that a lightning return stroke will produce an elve is correlated with the return stroke peak current, many large peak current strokes do not produce visible elves. Apart from the lightning peak current, elve production may depend on the return stroke speed, lightning altitude, and ionospheric conditions. In this work we investigate the detailed structure of lightning that gives rise to elves by analyzing the characteristics of VLF/LF lightning sferics in conjunction with optical elve observations. Lightning sferics were observed using an array of six VLF/LF receivers (1 MHz sample-rate) in Oklahoma, and elves were observed using two high-speed photometers pointed over the Oklahoma region: one located at Langmuir Laboratory, NM and the other at McDonald Observatory, TX. Hundreds of elves with coincident LF sferics were observed during the summer months of 2013. We present data comparing the characteristics of elve-producing and non-elve producing lightning as measured by LF sferics. In addition, we compare these sferic and elve observations with FDTD simulations to determine key properties of elve-producing lightning.

End-of-life vehicle recycling in China: Now and the future

NASA Astrophysics Data System (ADS)

Chen, Ming

2005-10-01

The volume of in-use vehicles in China will reach 32 million by the end of 2006 and the volume of end-of-life vehicles (ELVs) will be more than 1.5 million by the end of 2005. In 2001, China passed a law regulating the disposal and recycling of ELVs. Progress has been slow, with the rate of ELV dismantling just 10% at the beginning of 2004. However, a pilot industrial demonstration of ELV dismantling and disposal was established in Shanghai in 2005. In addition, Shanghai Volkswagen established a modern engine remanufacturing plant aiming at its after-sales market. This article reviews the ELV policy, law, and administration system in China; the ELV dismantling industry; the challenges and opportunities of ELV recycling; and the state-of-the-art of remanufacturing of ELVs in China.

General Environmental Verification Specification

NASA Technical Reports Server (NTRS)

Milne, J. Scott, Jr.; Kaufman, Daniel S.

2003-01-01

The NASA Goddard Space Flight Center s General Environmental Verification Specification (GEVS) for STS and ELV Payloads, Subsystems, and Components is currently being revised based on lessons learned from GSFC engineering and flight assurance. The GEVS has been used by Goddard flight projects for the past 17 years as a baseline from which to tailor their environmental test programs. A summary of the requirements and updates are presented along with the rationale behind the changes. The major test areas covered by the GEVS include mechanical, thermal, and EMC, as well as more general requirements for planning, tracking of the verification programs.

Fuzzy risk explicit interval linear programming model for end-of-life vehicle recycling planning in the EU.

PubMed

Simic, Vladimir

2015-01-01

End-of-life vehicles (ELVs) are vehicles that have reached the end of their useful lives and are no longer registered or licensed for use. The ELV recycling problem has become very serious in the last decade and more and more efforts are made in order to reduce the impact of ELVs on the environment. This paper proposes the fuzzy risk explicit interval linear programming model for ELV recycling planning in the EU. It has advantages in reflecting uncertainties presented in terms of intervals in the ELV recycling systems and fuzziness in decision makers' preferences. The formulated model has been applied to a numerical study in which different decision maker types and several ELV types under two EU ELV Directive legislative cases were examined. This study is conducted in order to examine the influences of the decision maker type, the α-cut level, the EU ELV Directive and the ELV type on decisions about vehicle hulks procuring, storing unprocessed hulks, sorting generated material fractions, allocating sorted waste flows and allocating sorted metals. Decision maker type can influence quantity of vehicle hulks kept in storages. The EU ELV Directive and decision maker type have no influence on which vehicle hulk type is kept in the storage. Vehicle hulk type, the EU ELV Directive and decision maker type do not influence the creation of metal allocation plans, since each isolated metal has its regular destination. The valid EU ELV Directive eco-efficiency quotas can be reached even when advanced thermal treatment plants are excluded from the ELV recycling process. The introduction of the stringent eco-efficiency quotas will significantly reduce the quantities of land-filled waste fractions regardless of the type of decision makers who will manage vehicle recycling system. In order to reach these stringent quotas, significant quantities of sorted waste need to be processed in advanced thermal treatment plants. Proposed model can serve as the support for the European vehicle recycling managers in creating more successful ELV recycling plans. Copyright © 2014 Elsevier Ltd. All rights reserved.

2008 NASA Range Safety Annual Report

NASA Technical Reports Server (NTRS)

Lamoreaux, Richard W.

2008-01-01

Welcome to the 2008 edition of the NASA Range Safety Annual Report. Funded by NASA Headquarters, this report provides a NASA Range Safety overview for current and potential range users. This year, along with full length articles concerning various subject areas, we have provided updates to standard subjects with links back to the 2007 original article. Additionally, we present summaries from the various NASA Range Safety Program activities that took place throughout the year, as well as information on several special projects that may have a profound impact on the way we will do business in the future. The sections include a program overview and 2008 highlights of Range Safety Training; Range Safety Policy; Independent Assessments and Common Risk Analysis Tools Development; Support to Program Operations at all ranges conducting NASA launch operations; a continuing overview of emerging Range Safety-related technologies; Special Interests Items that include recent changes in the ELV Payload Safety Program and the VAS explosive siting study; and status reports from all of the NASA Centers that have Range Safety responsibilities. As is the case each year, contributors to this report are too numerous to mention, but we thank individuals from the NASA Centers, the Department of Defense, and civilian organizations for their contributions. We have made a great effort to include the most current information available. We recommend that this report be used only for guidance and that the validity and accuracy of all articles be verified for updates. This is the third year we have utilized this web-based format for the annual report. We continually receive positive feedback on the web-based edition, and we hope you enjoy this year's product as well. It has been a very busy and productive year on many fronts as you will note as you review this report. Thank you to everyone who contributed to make this year a successful one, and I look forward to working with all of you in the years to come.

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.

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...

Optimal Recycling of Steel Scrap and Alloying Elements: Input-Output based Linear Programming Method with Its Application to End-of-Life Vehicles in Japan.

PubMed

Ohno, Hajime; Matsubae, Kazuyo; Nakajima, Kenichi; Kondo, Yasushi; Nakamura, Shinichiro; Fukushima, Yasuhiro; Nagasaka, Tetsuya

2017-11-21

Importance of end-of-life vehicles (ELVs) as an urban mine is expected to grow, as more people in developing countries are experiencing increased standards of living, while the automobiles are increasingly made using high-quality materials to meet stricter environmental and safety requirements. While most materials in ELVs, particularly steel, have been recycled at high rates, quality issues have not been adequately addressed due to the complex use of automobile materials, leading to considerable losses of valuable alloying elements. This study highlights the maximal potential of quality-oriented recycling of ELV steel, by exploring the utilization methods of scrap, sorted by parts, to produce electric-arc-furnace-based crude alloy steel with minimal losses of alloying elements. Using linear programming on the case of Japanese economy in 2005, we found that adoption of parts-based scrap sorting could result in the recovery of around 94-98% of the alloying elements occurring in parts scrap (manganese, chromium, nickel, and molybdenum), which may replace 10% of the virgin sources in electric arc furnace-based crude alloy steel production.

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.

Multiple Payload Ejector for Education, Science and Technology Experiments

NASA Technical Reports Server (NTRS)

Lechworth, Gary

2005-01-01

The education research community no longer has a means of being manifested on Space Shuttle flights, and small orbital payload carriers must be flown as secondary payloads on ELV flights, as their launch schedule, secondary payload volume and mass permits. This has resulted in a backlog of small payloads, schedule and cost problems, and an inability for the small payloads community to achieve routine, low-cost access to orbit. This paper will discuss Goddard's Wallops Flight Facility funded effort to leverage its core competencies in small payloads, sounding rockets, balloons and range services to develop a low cost, multiple payload ejector (MPE) carrier for orbital experiments. The goal of the MPE is to provide a low-cost carrier intended primarily for educational flight research experiments. MPE can also be used by academia and industry for science, technology development and Exploration experiments. The MPE carrier will take advantage of the DARPAI NASA partnership to perform flight testing of DARPA s Falcon small, demonstration launch vehicle. The Falcon is similar to MPE fiom the standpoint of focusing on a low-cost, responsive system. Therefore, MPE and Falcon complement each other for the desired long-term goal of providing the small payloads community with a low-cost ride to orbit. The readiness dates of Falcon and MPE are complementary, also. MPE is being developed and readied for flight within 18 months by a small design team. Currently, MPE is preparing for Critical Design Review in fall 2005, payloads are being manifested on the first mission, and the carrier will be ready for flight on the first Falcon demonstration flight in summer, 2006. The MPE and attached experiments can weigh up to 900 lb. to be compatible with Falcon demonstration vehicle lift capabilities fiom Wallops, and will be delivered to the Falcon demonstration orbit - 100 nautical mile circular altitude.

End-of-Life vehicle recovery in china: Consideration and innovation following the EU ELV directive

NASA Astrophysics Data System (ADS)

Chen, Ming; Zhang, Fan

2009-03-01

Implementation of the EU’s end-of-life vehicle (ELV) directive eight years ago had a profound influence on China’s automotive industry, leading to the consideration of concepts such as extended producer responsibility. It also provided some impetus for ELV recycling industry developments within China. This article provides insight into current thinking within China about ELV recycling as well as vehicle recovery activities.

Future Concepts for Integrating the Space Launch System and the Multi-Purpose Crew Vehicle into a Reusable Space Transportation Infrastructure

NASA Technical Reports Server (NTRS)

Smitherman, David; Woodcock, Gordon

2012-01-01

A space transportation infrastructure is described that utilizes the Space Launch System (SLS), the Mulit-Purpose Crew Vehicle (MPCV), the International Space Station (ISS), and propellant depot servicing platforms to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicle (ELV) systems such as the Delta IV Heavy, Atlas V, and Falcon 9, for commercial crew, cargo, and propellant launches to a Low-Earth-Orbit (LEO) Depot and/or the ISS. The SLS provides all payload and propellant launches to the Earth-Moon Langrange Point 1 (EML1) Depot to support new reusable in-space transportation vehicles. The ISS or follow-on LEO Depot supports missions to Geosynchronous Earth Orbit (GEO) for satellite servicing and to Earth-Moon L1 for EML1 Depot missions. The EML1 Depot supports Lunar, Earth-Sun L2 (ESL2), Asteroid, and Mars missions. New vehicle design concepts are presented that can be launched utilizing the SLS and current ELV systems. These new reusable vehicle concepts include a Crew Transfer Vehicle (CTV) derived from the MPCV and a reusable Cryogenic Propulsion Stage (CPS) for crew transportation between the LEO Depot, EML1 Depot and missions beyond the Earth-Moon vicinity; a new reusable Lunar Lander for crew transportation between the EML1 Depot and the lunar surface; and a new reusable Deep Space Habitat (DSH) with a CTV to support crew missions from the EML1 Depot to ESL2, Asteroids, and a Mars Orbital Depot. The LEO Depot, EML1 Depot, and Mars Orbital Depot are based on International Space Station (ISS) heritage hardware. Data provided includes the number of launches required for each mission utilizing SLS and current ELV systems (Delta IV Heavy or equivalent) and the approximate vehicle masses and propellant requirements. Also included is a discussion on affordability with ideas on technologies that could reduce the number of launches required and thoughts on how this infrastructure might be implemented incrementally over the next few decades. The potential benefits of this infrastructure include competitive bidding for ELV flights and propellant services, development of new reusable in-space vehicles, and development of a robust multiuse infrastructure that can support many government and commercial missions simultaneously.

Estimated intensity of the EMP from lightning discharges necessary for elves initiation based on balloon experiment

NASA Astrophysics Data System (ADS)

Kondo, S.; Yoshida, A.; Takahashi, Y.; Chikada, S.; Adachi, T.; Sakanoi, T.

2007-12-01

Transient optical phenomena in the mesosphere and lower ionosphere called transient luminous events (TLEs) have been investigated extensively since the first discovery in 1989. In the lower ionosphere, elves are generated by the electromagnetic pulses (EMPs) radiated from the intense lightning current. On the ground-based observation, cameras can not always identify the occurrence of elves because elves emission is sometimes reduced significantly by the atmosphere and blocked by clouds. Therefore, it has been difficult to determine the threshold of intensity of EMPs necessary for initiation of elves. We simultaneously carried out optical and sferics measurements for TLEs and lightning discharges using a high altitude balloon launched at Sanriku Balloon Center on the night of August 25 / 26 in 2006. We fixed four CCD cameras on the gondola, each of which had horizontal FOV of ~100 degree. They cover 360 degree in horizontal direction and imaged the TLEs without atmospheric extinction nor blocking by clouds. The frame rate is 30 fps. We installed three dipole antennas at the gondola, which received the vertical and horizontal electric fields radiated from lightning discharges. The frequency range of the VLF receiver is 1-25 kHz. We also make use of VLF sferics data obtained by ground-based antennas located at Tohoku University in Sendai. We picked up six elves from the image data set obtained by the CCD cameras, and examined the maximum amplitudes of the vertical electric field for 22 lightning discharge events including the six elves events observed both at the balloon and at Sendai. It is found that the maximum amplitudes of the vertical electric field in the five elves events are much larger than those in the other lightning events. We estimate the intensity of the radiated electric field necessary for elves. About one elves event, we don't see intense vertical electric field in the balloon data.

Effects of Solar Activities on the Transient Luminous Events

NASA Astrophysics Data System (ADS)

Wu, Y.; Williams, E.; Chou, J.; Lee, L.; Huang, S.; Chang, S.; Chen, A. B.; Kuo, C.; Su, H.; Hsu, R.; Frey, H. U.; Takahashi, Y.; Lee, L.

2013-12-01

The Imager of Sprite and Upper Atmosphere Lightning (ISUAL) onboard the Formosat-2 was launched in May 2004; since then, it has continuously observed transient luminous events (TLEs) within the +/-60 degree of latitude for nearly 10 years. Due to ISUAL's long-term observations, the possible correlation between the TLE and the solar activity can be explored. Among the ISUAL TLEs, elves, which occur at the mesospheric altitude ~90 km and are caused by the heating incurred by the lightning-launched electromagnetic pulse of the lower ionosphere boundary are the most numerous and are the most suitable for this type of study. In previous studies, the elve distribution has proved to be a good surrogate for the lightning with exceptional peak current globally. ISUAL records the occurrence time and the height and location of elves, and the spectral emission intensities at six different band pass including the FUV N2 Lyman-Birge-Hopfield (LBH) band, which is a dominant emission in elves. The LBH intensity not only reflects the peak current of parent lightning, but may also represent the solar-activity-driven-lighting's perturbation to the ionosphere. In this study, we first examine whether the 11-year solar cycle affects the elve activity and altitude by analyzing the elve occurrence rates and heights in different latitudinal regions. To avoid the climatological and instrumental biases in the elve observations, the effects arising from the ENSO and moonlight must be carefully eliminated. Besides, we will discuss the elve variation in shorter time scale due to strong and sudden change of solar activity. Since the ion density of the mesosphere at mid-latitude may be significantly altered during/after a strong corona mass ejection (CME).Furthermore, it has been proven that the changes in the solar X-ray flux dominate the variations in the conductivity profile within the upper characteristic ELF layer (the 90-100km portion of the E-region). we will compare the variation of emission intensity of elves with and without intense CME/x-ray flux events to quantify the possible effects of ionospheric perturbations due to solar activity. We have selected elves over the winter storm track in the Pacific Ocean region northeast of Japan due to the strong elve activity there during northern hemisphere winters in order to make sure the sufficient events for statistical analysis. The peak current of the parent lightning for the ISUAL elves can be inferred from the lightning energy recorded by the WWLLN. With the inferred peak current, the LBH band emission intensity in elves can be computed. Finally, the theoretical and the observed LBH band intensity for elves are to be compared; the difference may come from the effect of intense CME/x-ray flux .Details of the data analyses and the preliminary results will be presented fully in the report.

SLS Payload Transportation Beyond LEO

NASA Technical Reports Server (NTRS)

Creech, S. D.; Baker, J. D.; Jackman, A. L.; Vane, G.

2017-01-01

NASA has successfully completed the Critical Design Review (CDR) of the heavy lift Space Launch System (SLS) and is working towards the first flight of the vehicle in 2018. SLS will begin flying crewed missions with an Orion capsule to the lunar vicinity every year after the first 2 flights starting in the early 2020's. As early as 2021, in addition to delivering an Orion capsule to a cislunar destination, SLS will also deliver ancillary payload, termed "Co-manifested Payload (CPL)", with a mass of at least 5.5 mT and volume up to 280 m3 simultaneously to that same destination. Later SLS flights have a goal of delivering as much as 10 mT of CPL to cislunar destinations. In addition to cislunar destinations, SLS flights may deliver non-crewed, science-driven missions with Primary Payload (PPL) to more distant destinations. SLS PPL missions will utilize a unique payload fairing offering payload volume (ranging from 320 m3 to 540 m3) that greatly exceeds the largest existing Expendable Launch Vehicle (ELV) fairing available. The Characteristic Energy (C3) offered by the SLS system will generate opportunities to deliver up to 40 mT to cislunar space, and deliver double PPL mass or de-crease flight time by half for some outer planet destinations when compared to existing capabilities. For example, SLS flights may deliver the Europa Clipper to a Jovian destination in under 3 years by the mid 2020's, compared to the 7+ years cruise time required for current launch capabilities. This presentation will describe ground and flight accommodations, interfaces, resources, and performance planned to be made available to potential CPL and PPL science users of SLS. In addition, this presentation should promote a dialogue between vehicle developers, potential payload users, and funding sources in order to most efficiently evolve required SLS capabilities to meet diverse payload needs as they are identified over the next 35 years and beyond.

Interval-parameter chance-constraint programming model for end-of-life vehicles management under rigorous environmental regulations.

PubMed

Simic, Vladimir

2016-06-01

As the number of end-of-life vehicles (ELVs) is estimated to increase to 79.3 million units per year by 2020 (e.g., 40 million units were generated in 2010), there is strong motivation to effectively manage this fast-growing waste flow. Intensive work on management of ELVs is necessary in order to more successfully tackle this important environmental challenge. This paper proposes an interval-parameter chance-constraint programming model for end-of-life vehicles management under rigorous environmental regulations. The proposed model can incorporate various uncertainty information in the modeling process. The complex relationships between different ELV management sub-systems are successfully addressed. Particularly, the formulated model can help identify optimal patterns of procurement from multiple sources of ELV supply, production and inventory planning in multiple vehicle recycling factories, and allocation of sorted material flows to multiple final destinations under rigorous environmental regulations. A case study is conducted in order to demonstrate the potentials and applicability of the proposed model. Various constraint-violation probability levels are examined in detail. Influences of parameter uncertainty on model solutions are thoroughly investigated. Useful solutions for the management of ELVs are obtained under different probabilities of violating system constraints. The formulated model is able to tackle a hard, uncertainty existing ELV management problem. The presented model has advantages in providing bases for determining long-term ELV management plans with desired compromises between economic efficiency of vehicle recycling system and system-reliability considerations. The results are helpful for supporting generation and improvement of ELV management plans. Copyright © 2016 Elsevier Ltd. All rights reserved.

The Implementation of Payload Safety in an Operational Environment

NASA Technical Reports Server (NTRS)

Cissom, R. D.; Horvath, Tim J.; Watson, Kristi S.; Rogers, Mark N. (Technical Monitor); Vanhooser, T. (Technical Monitor)

2002-01-01

The objective of this paper is to define the safety life-cycle process for a payload beginning with the output of the Payload Safety Review Panel and continuing through the life of the payload on-orbit. It focuses on the processes and products of the operations safety implementation through the increment preparations and real-time operations processes. In addition, the paper addresses the role of the Payload Operations and Integration Center and the interfaces to the International Partner Payload Control Centers.

Comparison of static end-expiratory and effective lung volumes for gas exchange in healthy and surfactant-depleted lungs.

PubMed

Albu, Gergely; Wallin, Mats; Hallbäck, Magnus; Emtell, Per; Wolf, Andrew; Lönnqvist, Per-Arne; Göthberg, Sylvia; Peták, Ferenc; Habre, Walid

2013-07-01

Effective lung volume (ELV) for gas exchange is a new measure that could be used as a real-time guide during controlled mechanical ventilation. The authors established the relationships of ELV to static end-expiratory lung volume (EELV) with varying levels of positive end-expiratory pressure (PEEP) in healthy and surfactant-depleted rabbit lungs. Nine rabbits were anesthetized and ventilated with a modified volume-controlled mode where periods of five consecutive alterations in inspiratory/expiratory ratio (1:2-1.5:1) were imposed to measure ELV from the corresponding carbon dioxide elimination traces. EELV and the lung clearance index were concomitantly determined by helium wash-out technique. Airway and tissue mechanics were assessed by using low-frequency forced oscillations. Measurements were collected at PEEP 0, 3, 6, and 9 cm H2O levels under control condition and after surfactant depletion by whole-lung lavage. ELV was greater than EELV at all PEEP levels before lavage, whereas there was no evidence for a difference in the lung volume indices after surfactant depletion at PEEP 6 or 9 cm H2O. Increasing PEEP level caused significant parallel increases in both ELV and EELV levels, decreases in ventilation heterogeneity, and improvement in airway and tissue mechanics under control condition and after surfactant depletion. ELV and EELV exhibited strong and statistically significant correlations before (r=0.84) and after lavage (r=0.87). The parallel changes in ELV and EELV with PEEP in healthy and surfactant-depleted lungs support the clinical value of ELV measurement as a bedside tool to estimate dynamic changes in EELV in children and infants.

ELVES Research at the Pierre Auger Observatory: Optical Emission Simulation and Time Evolution, WWLLN-LIS-Auger Correlations, and Double ELVES Observations and Simulation.

NASA Astrophysics Data System (ADS)

Merenda, K. D.

2016-12-01

Since 2013, the Pierre Auger Cosmic Ray Observatory in Mendoza, Argentina, extended its trigger algorithm to detect emissions of light consistent with the signature from very low frequency perturbations due to electromagnetic pulse sources (ELVES). Correlations with the World Wide Lightning Location Network (WWLLN), the Lightning Imaging Sensor (LIS) and simulated events were used to assess the quality of the reconstructed data. The FD is a pixel array telescope sensitive to the deep UV emissions of ELVES. The detector provides the finest time resolution of 100 nanoseconds ever applied to the study of ELVES. Four eyes, separated by approximately 40 kilometers, consist of six telescopes and span a total of 360 degrees of azimuth angle. The detector operates at night when storms are not in the field of view. An existing 3D EMP Model solves Maxwell's equations using a three dimensional finite-difference time-domain model to describe the propagation of electromagnetic pulses from lightning sources to the ionosphere. The simulation also provides a projection of the resulting ELVES onto the pixel array of the FD. A full reconstruction of simulated events is under development. We introduce the analog signal time evolution comparison between Auger reconstructed data and simulated events on individual FD pixels. In conjunction, we will present a study of the angular distribution of light emission around the vertical and above the causative lightning source. We will also contrast, with Monte Carlo, Auger double ELVES events separated by at most 5 microseconds. These events are too short to be explained by multiple return strokes, ground reflections, or compact intra-cloud lightning sources. Reconstructed ELVES data is 40% correlated to WWLLN data and an analysis with the LIS database is underway.

End-of-Life Vehicle Dismantling and Recycling Enterprises: Developing Directions in China

NASA Astrophysics Data System (ADS)

Wang, Lu; Chen, Ming

2013-08-01

End-of-life vehicle (ELV) dismantling and recycling enterprises are the final disposer of the life-cycle process of vehicles. ELV collecting, dismantling technology, and waste disposal directly affect the recovery rate and the friendliness of vehicles toward the environment. China law stipulates that, by 2017, the recovery rate of vehicles should not be less than 95%, and the recycling rate of materials should not be less than 85%. Therefore, knowing the practical running state of such enterprises is needed. This study investigated four ELV dismantling and recycling enterprises in the Yangzi delta district in China and surveyed the ELV collecting, dismantling technology, policy implementation, and running difficulties. After the comparison with the developed countries, the relevant experiences were drawn, and effective measures were put forward to meet the aims stipulated in the law based on the current practical ELV market in China.

Development of an end-of-life vehicle recovery model using system dynamics and future research needs

NASA Astrophysics Data System (ADS)

Mohamad-Ali, N.; Ghazilla, R. A. R.; Abdul-Rashid, S. H.; Sakundarini, N.; Ahmad-Yazid, A.; Stephenie, L.

2017-06-01

The implementation of end-of-life vehicle (ELV) recovery policy in Malaysia has led vehicle manufacturers to look at different ways to improve design and development of vehicles. Nowadays, it is crucial to incorporate end-of-life (EOL) design strategies into the vehicle design in order to enhance the effectiveness of the ELV recovery network. Although recent studies have shown that product design has a significant effect on the product recovery rate, there is a lack of studies on how EOL design strategies affects the effectiveness of ELV recovery, particularly when there are dynamic changes in the behaviour of the product recovery network. Thus, in this study, we developed a preliminary model based on the system dynamics approach in order to predict the effectiveness of ELV recovery in response to dynamic changes of various factors (including EOL design strategies) in the business environment. We developed this model based on preliminary data that we had gathered from unstructured interviews with the key stakeholders of ELV management in Malaysia. We believe that our model will greatly benefit product designers in incorporating the appropriate EOL design strategies in order to boost ELV recovery effectiveness in Malaysia.

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.

Space transportation system payload safety guidelines handbook

NASA Technical Reports Server (NTRS)

1976-01-01

This handbook provides the payload developer with a uniform description and interpretation of the potential hazards which may be caused by or associated with a payload element, operation, or interface with other payloads or with the STS. It also includes guidelines describing design or operational safety measures which suggest means of alleviating a particular hazard or group of hazards, thereby improving payload safety.

Abnormalities in arterial-ventricular coupling in older healthy persons are attenuated by sodium nitroprusside.

PubMed

Chantler, Paul D; Nussbacher, Amit; Gerstenblith, Gary; Schulman, Steven P; Becker, Lewis C; Ferrucci, Luigi; Fleg, Jerome L; Lakatta, Edward G; Najjar, Samer S

2011-05-01

The coupling between arterial elastance (E(A); net afterload) and left ventricular elastance (E(LV); pump performance), known as E(A)/E(LV), is a key determinant of cardiovascular performance and shifts during exercise due to a greater increase in E(LV) versus E(A). This normal exercise-induced reduction in E(A)/E(LV) decreases with advancing age. We hypothesized that sodium nitroprusside (SNP) can acutely ameliorate the age-associated deficits in E(A)/E(LV). At rest and during graded exercise to exhaustion, E(A) was characterized as end-systolic pressure/stroke volume and E(LV) as end-systolic pressure/end-systolic volume. Resting E(A)/E(LV) did not differ between old (70 ± 8 yr, n = 15) and young (30 ± 5 yr, n = 17) subjects because of a tandem increase in E(A) and E(LV) in older subjects. During peak exercise, a blunted increase in E(LV) in old (7.8 ± 3.1 mmHg/ml) versus young (11.4 ± 6.5 mmHg/ml) subjects blunted the normal exercise-induced decline in E(A)/E(LV) in old (0.25 ± 0.11) versus young (0.16 ± 0.05) subjects. SNP administration to older subjects lowered resting E(A)/E(LV) by 31% via a reduction in E(A) (10%) and an increase in E(LV) (47%) and lowered peak exercise E(A)/E(LV) (36%) via an increase in E(LV) (68%) without a change in E(A). Importantly, SNP attenuated the age-associated deficits in E(A)/E(LV) and E(LV) during exercise, and at peak exercise E(A)/E(LV) in older subjects on drug administration did not differ from young subjects without drug administration. In conclusion, some age-associated deficiencies in E(A)/E(LV), E(A), and E(LV), in older subjects can be acutely abolished by SNP infusion. This is relevant to common conditions in older subjects associated with a significant impairment of exercise performance such as frailty or heart failure with preserved ejection fraction.

Safety policy and requirements for payloads using the Space Transportation System (STS)

NASA Technical Reports Server (NTRS)

1982-01-01

The Space Transportation Operations (STO) safety policy is to minimize STO involvement in the payload and its GSE (ground support equipment) design process while maintaining the assurance of a safe operation. Requirements for assuring payload mission success are the responsibility of the payload organization and are beyond the scope of this document. The intent is to provide the overall safety policies and requirements while allowing for negotiation between the payload organization and the STO operator in the method of implementation of payload safety. This revision provides for a relaxation in the monitoring requirements for inhibits, allows the payload organization to pursue design options and reflects, additionally, some new requirements. As of the issue date of this NHB, payloads which have completed the formal safety assessment reviews of their preliminary design on the basis of the May 1979 issue will be reassessed for compliance with the above changes.

Safety policy and requirements for payloads using the space transportation system

NASA Technical Reports Server (NTRS)

1989-01-01

The safety policy and requirements are established applicable to the Space Transportation System (STS) payloads and their ground support equipment (GSE). The requirements are intended to protect flight and ground personnel, the STS, other payloads, GSE, the general public, public-private property, and the environment from payload-related hazards. The technical and system safety requirements applicable to STS payloads (including payload-provided ground and flight supports systems) during ground and flight operations are contained.

Sustainable design for automotive products: dismantling and recycling of end-of-life vehicles.

PubMed

Tian, Jin; Chen, Ming

2014-02-01

The growth in automotive production has increased the number of end-of-life vehicles (ELVs) annually. The traditional approach ELV processing involves dismantling, shredding, and landfill disposal. The "3R" (i.e., reduce, reuse, and recycle) principle has been increasingly employed in processing ELVs, particularly ELV parts, to promote sustainable development. The first step in processing ELVs is dismantling. However, certain parts of the vehicle are difficult to disassemble and use in practice. The extended producer responsibility policy requires carmakers to contribute in the processing of scrap cars either for their own developmental needs or for social responsibility. The design for dismantling approach can be an effective solution to the existing difficulties in dismantling ELVs. This approach can also provide guidelines in the design of automotive products. This paper illustrates the difficulty of handling polymers in dashboards. The physical properties of polymers prevent easy separation and recycling by using mechanical methods. Thus, dealers have to rely on chemical methods such as pyrolysis. Therefore, car designers should use a single material to benefit dealers. The use of materials for effective end-of-life processing without sacrificing the original performance requirements of the vehicle should be explored. Copyright © 2013 Elsevier Ltd. All rights reserved.

Are scarce metals in cars functionally recycled?

PubMed

Andersson, Magnus; Ljunggren Söderman, Maria; Sandén, Björn A

2017-02-01

Improved recycling of end-of-life vehicles (ELVs) may serve as an important strategy to address resource security risks related to increased global demand for scarce metals. However, in-depth knowledge of the magnitude and fate of such metals entering ELV recycling is lacking. This paper quantifies input of 25 scarce metals to Swedish ELV recycling, and estimates the extent to which they are recycled to material streams where their metal properties are utilised, i.e. are functionally recycled. Methodologically, scarce metals are mapped to main types of applications within newly produced Swedish car models and subsequently, material flow analysis of ELV waste streams is used as basis for identifying pathways of these applications and assessing whether contained metals are functionally recycled. Results indicate that, of the scarce metals, only platinum may be functionally recycled in its main application. Cobalt, gold, manganese, molybdenum, palladium, rhodium and silver may be functionally recycled depending on application and pathways taken. For remaining 17 metals, functional recycling is absent. Consequently, despite high overall ELV recycling rates of materials in general, there is considerable risk of losing ELV scarce metals to carrier metals, construction materials, backfilling materials and landfills. Given differences in the application of metals and identified pathways, prospects for increasing functional recycling are discussed. Copyright © 2016 Elsevier Ltd. All rights reserved.

The development and prospects of the end-of-life vehicle recycling system in Taiwan.

PubMed

Chen, Kuan-chung; Huang, Shih-han; Lian, I-wei

2010-01-01

Automobiles usually contain toxic substances, such as lubricants, acid solutions and coolants. Therefore, inappropriate handling of end-of-life vehicles (ELVs) will result in environmental pollution. ELV parts, which include metallic and non-metallic substances, are increasingly gaining recycling value due to the recent global shortage of raw materials. Hence, the establishment of a proper recycling system for ELVs will not only reduce the impact on the environment during the recycling process, but it will also facilitate the effective reuse of recycled resources. Prior to 1994, the recycling of ELVs in Taiwan was performed by related operators in the industry. Since the publishing of the "End-of-life vehicle recycling guidelines" under the authority of the Waste Disposal Act by the Environmental Protection Administration (EPA) in 1994, the recycling of ELVs in Taiwan has gradually become systematic. Subsequently, the Recycling Fund Management Board (RFMB) of the EPA was established in 1998 to collect a Collection-Disposal-Treatment Fee (recycling fee) from responsible enterprises for recycling and related tasks. Since then, the recycling channels, processing equipment, and techniques for ELVs in Taiwan have gradually become established. This paper reviews the establishment of the ELV recycling system, analyzes the current system and its performance, and provides some recommendations for future development. The reduction of auto shredder residue (ASR) is a key factor in maximizing the resource recovery rate and recycling efficiency. The RFMB needs to provide strong economic incentives to further increase the recycling rate and to encourage the automobile industry to design and market greener cars. 2010 Elsevier Ltd. All rights reserved.

Real Time Maintenance Approval and Required IMMT Coordination

NASA Technical Reports Server (NTRS)

Burchell, S.

2016-01-01

Payloads are assessed for nominal operations. Payload Developers have the option of performing a maintenance hazard assessment (MHA) for potential maintenance activities. When POIC (Payload Operations and Integration Center) Safety reviews an OCR calling for a maintenance procedure, we cannot approve it without a MHA. If no MHA exists, we contact MER (Mission Evaluation Room) Safety. Depending on the nature of the problem, MER Safety has the option to: Analyze and grant approval themselves; Direct the payload back to the ISRP (Integrated Safety Review Panel); Direct the payload to the IMMT (Increment Mission Management Team).

Stereo Reconstruction of ELVES at the Pierre Auger Observatory

NASA Astrophysics Data System (ADS)

Mussa, R.; Tonachini, A. S.

2013-12-01

The Pierre Auger Observatory, located in Malargue (Argentina), is the world's largest facility (3000 km2) for the study of Ultra High Energy Cosmic Rays (E>10^18 eV). The four sites of the Fluorescence Detector (covering a field of view of 30x180 degrees) are continuously observing the night sky with 100 ns time resolution and a space resolution of about 1 degree. In May 2005, the first ELVES candidate was serendipitously observed by the FD, which is designed to detect the electromagnetic component of cosmic ray showers and to reject lightning. Since March 2013, the Auger Observatory has implemented a special trigger dedicated to the detection of ELVES, whose topology (a rapidly evolving ring) is quite different from the one of cosmic ray events. This allows to record events with high efficiency and unprecedented accuracy. The average distance between two eyes, about 40 km, allows stereo imaging of a large fraction of ELVES candidate events. More than 100 ELVES candidates from the first 6 months of data taking will be shown.

Implementation Procedure for STS Payloads, System Safety Requirements

NASA Technical Reports Server (NTRS)

1979-01-01

Guidelines and instructions for the implementation of the SP&R system safety requirements applicable to STS payloads are provided. The initial contact meeting with the payload organization and the subsequent safety reviews necessary to comply with the system safety requirements of the SP&R document are described. Waiver instructions are included for the cases in which a safety requirement cannot be met.

Expendable launch vehicle transportation for the Space Station

NASA Technical Reports Server (NTRS)

Corban, Robert R.

1988-01-01

ELVs are presently evaluated as major components of the NASA Space Station's logistics transportation system, augmenting the cargo capacity of the Space Shuttle in support of Station productivity and operational flexibility. The ELVs in question are the Delta II, Atlas II, Titan III, Titan IV, Shuttle-C (unmanned cargo development), European Ariane 5, and Japanese H-II, as well as smaller launch vehicles and OTVs. Early definition of ELV program impacts will preclude the potentially excessive costs of future Space Station modifications.

On-field investigation and process modelling of end-of-life vehicles treatment in the context of Italian craft-type authorized treatment facilities.

PubMed

Berzi, Lorenzo; Delogu, Massimo; Giorgetti, Alessandro; Pierini, Marco

2013-04-01

The present article analyses the current situation of End-of-Life-of-Vehicles (ELVs) management in Europe, with particular attention on Italian condition. Similarly to other European countries, metal recycling is the main activity of the whole system, but such situation is evolving due to the 2000/53/EC Directive, which sets out targets for Reuse, Recycling and Recovery of ELVs. Due to the relevance of the ELVs problem, in 2008 Italian Ministry of Environment subscribed a framework agreement with competent stakeholders as carmakers, dismantlers, shredders. The main result is an industrial plan to promote (amongst other objectives) technological progress for residual waste (Automotive Shredder Residue-ASR) treatment. According with Italian Trial 2006 analysis about ELVs, Reuse and Recycling rate is currently estimated to be about 81%. At the present time, dismantling plants constitute the first collection points for ELVs; for this reason, during 2009 an investigation has been done over a number of ten Authorized Treatment Facilities (ATFs) operating in Italy. The first step of the analysis was aimed to find out major practices and methods through observations of ATFs activities and interviews to operators. Furthermore, the depollution and dismantling treatments of about 70 different ELVs have been observed and timed in detail over a period of three months. The results included the identification of most relevant critical issues in ELVs treatment, such as distortions between scrapping activities and Directive's regulation, and the assessment of the time and of the resources needed to perform each operation. In the second step of the survey, a process simulation model has been built on the basis of such data. The model was aimed to include the real variability and all the uncertainties that are typical of dismantling activities; it is intended as a tool for process layout planning and for its management. Some control parameters have been introduced; these are able to dynamically modify process path depending on ELVs queues and priorities. The model can also be used for the economic assessments of single operations or of the whole treatment activity. Copyright © 2012 Elsevier Ltd. All rights reserved.

Exosome-Like Vesicles Derived from Adipose Tissue Provide Biochemical Cues for Adipose Tissue Regeneration.

PubMed

Dai, Minjia; Yu, Mei; Zhang, Yan; Tian, Weidong

2017-11-01

There is an emerging need for soft tissue replacements in the field of reconstructive surgery for the treatment of congenital deformities, posttraumatic repair, and cancer rehabilitation. Previous studies have shown that the bioactive adipose tissue extract can induce adipogenesis without additional stem cells or growth factors. In this study, we innovatively investigated whether exosome-like vesicles derived from adipose tissue (ELV-AT) could direct stem cell differentiation and trigger adipose tissue regeneration. In vitro, ELV-AT can induce adipogenesis of adipose-derived stem cells and promote proliferation, migration, and angiogenic potential of the aorta endothelial cells. In vivo, ELV-AT were transplanted to a chamber on the back of nude mice and neoadipose tissues were formed. Our findings indicated that ELV-AT could be used as a cell-free therapeutic approach for adipose tissue regeneration.

Effect of Cobicistat on Tenofovir Disoproxil Fumarate (TDF): What Is True for TAF May Also Be True for TDF.

PubMed

Cattaneo, Dario; Minisci, Davide; Baldelli, Sara; Mazzali, Cristina; Giacomelli, Andrea; Milazzo, Laura; Meraviglia, Paola; Resnati, Chiara; Rizzardini, Giuliano; Clementi, Emilio; Galli, Massimo; Gervasoni, Cristina

2018-01-01

The dose of tenofovir alafenamide is reduced from 25 to 10 mg daily when given with boosting agents. However, such dose reduction has never been adopted for tenofovir disoproxil fumarate (TDF). In this study, we aim to quantify the effect of cobicistat (COBI) both on tenofovir concentrations and TDF durability in real life setting. HIV-positive patients receiving TDF-containing antiretroviral therapies with at least 1 assessment of tenofovir plasma trough concentrations were included in the study. Univariate and multivariate regression analyses were performed considering tenofovir concentration as the dependent variable and clinical characteristics as independent covariates. Subsequently, survival and Cox analyses were performed considering as the primary outcome TDF discontinuation for any reasons. Patients were given TDF with protease inhibitors/ritonavir (n = 212), non-nucleoside reverse transcriptase inhibitors (n = 176), integrase inhibitors (dolutegravir or raltegravir, n = 46), or with elvitegravir/COBI (ELV/COBI) (n = 76). By multivariate analysis, concomitant antiretroviral therapies resulted significantly associated with tenofovir levels, with the highest drug concentrations measured in patients given ELV/COBI. By survival analysis, we found that patients given TDF with ELV/COBI had the lowest rate of drug durability. Overall, these patients had a 2.3-fold increased risk to experience TDF discontinuation. Coadministration with COBI resulted in significantly higher tenofovir concentrations and higher TDF discontinuation compared with other antiretroviral regimens. Accordingly, the possibility that the lack of proper dose adjustment for TDF when given with COBI might have biased the safety comparisons with tenofovir alafenamide during registrative trials cannot be ruled out.

The Cost-Optimal Size of Future Reusable Launch Vehicles

NASA Astrophysics Data System (ADS)

Koelle, D. E.

2000-07-01

The paper answers the question, what is the optimum vehicle size — in terms of LEO payload capability — for a future reusable launch vehicle ? It is shown that there exists an optimum vehicle size that results in minimum specific transportation cost. The optimum vehicle size depends on the total annual cargo mass (LEO equivalent) enviseaged, which defines at the same time the optimum number of launches per year (LpA). Based on the TRANSCOST-Model algorithms a wide range of vehicle sizes — from 20 to 100 Mg payload in LEO, as well as launch rates — from 2 to 100 per year — have been investigated. It is shown in a design chart how much the vehicle size as well as the launch rate are influencing the specific transportation cost (in MYr/Mg and USS/kg). The comparison with actual ELVs (Expendable Launch Vehicles) and Semi-Reusable Vehicles (a combination of a reusable first stage with an expendable second stage) shows that there exists only one economic solution for an essential reduction of space transportation cost: the Fully Reusable Vehicle Concept, with rocket propulsion and vertical take-off. The Single-stage Configuration (SSTO) has the best economic potential; its feasibility is not only a matter of technology level but also of the vehicle size as such. Increasing the vehicle size (launch mass) reduces the technology requirements because the law of scale provides a better mass fraction and payload fraction — practically at no cost. The optimum vehicle design (after specification of the payload capability) requires a trade-off between lightweight (and more expensive) technology vs. more conventional (and cheaper) technology. It is shown that the the use of more conventional technology and accepting a somewhat larger vehicle is the more cost-effective and less risky approach.

Commercial ELV services and the National Aeronautics and Space Administration - Concord or discord?

NASA Technical Reports Server (NTRS)

Frankle, Edward A.

1988-01-01

In implementation of the U.S. policy to foster and encourage the commercial expendable launch vehicle (ELV) industry, tensions have developed between the industry and U.S. Government agencies in two distinct areas: industry use of government facilities and government purchase of commercial ELV services. The reasons for the tensions and discrete legal problems for each area are identified and discussed. Specifically, in the use of government facilities area, issues of insurance and indemnification for third-party liability and government property, concerns over priority and scheduling, and dispute-resolution procedures are discussed. In the area of government purchase of ELV launch services, a comparison is made between a launch service purchase and prior procurement practice. In all areas, the conclusion is reached that while problems still exist, they generally are understood and great progress has been made toward their resolution.

Manned space flight nuclear system safety. Volume 4: Space shuttle nuclear system transportation. Part 1: Space shuttle nuclear safety

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the nuclear safety aspects (design and operational considerations) in the transport of nuclear payloads to and from earth orbit by the space shuttle is presented. Three representative nuclear payloads used in the study were: (1) the zirconium hydride reactor Brayton power module, (2) the large isotope Brayton power system and (3) small isotopic heat sources which can be a part of an upper stage or part of a logistics module. Reference data on the space shuttle and nuclear payloads are presented in an appendix. Safety oriented design and operational requirements were identified to integrate the nuclear payloads in the shuttle mission. Contingency situations were discussed and operations and design features were recommended to minimize the nuclear hazards. The study indicates the safety, design and operational advantages in the use of a nuclear payload transfer module. The transfer module can provide many of the safety related support functions (blast and fragmentation protection, environmental control, payload ejection) minimizing the direct impact on the shuttle.

STS safety approval process for small self-contained payloads

NASA Technical Reports Server (NTRS)

Gum, Mary A.

1988-01-01

The safety approval process established by the National Aeronautics and Space Administration for Get Away Special (GAS) payloads is described. Although the designing organization is ultimately responsible for the safe operation of its payload, the Get Away Special team at the Goddard Space Flight Center will act as advisors while iterative safety analyses are performed and the Safety Data Package inputs are submitted. This four phase communications process will ultimately give NASA confidence that the GAS payload is safe, and successful completion of the Phase 3 package and review will clear the way for flight aboard the Space Transportation System orbiter.

Commonalities and Differences in Functional Safety Systems Between ISS Payloads and Industrial Applications

NASA Astrophysics Data System (ADS)

Malyshev, Mikhail; Kreimer, Johannes

2013-09-01

Safety analyses for electrical, electronic and/or programmable electronic (E/E/EP) safety-related systems used in payload applications on-board the International Space Station (ISS) are often based on failure modes, effects and criticality analysis (FMECA). For industrial applications of E/E/EP safety-related systems, comparable strategies exist and are defined in the IEC-61508 standard. This standard defines some quantitative criteria based on potential failure modes (for example, Safe Failure Fraction). These criteria can be calculated for an E/E/EP system or components to assess their compliance to requirements of a particular Safety Integrity Level (SIL). The standard defines several SILs depending on how much risk has to be mitigated by a safety-critical system. When a FMECA is available for an ISS payload or its subsystem, it may be possible to calculate the same or similar parameters as defined in the 61508 standard. One example of a payload that has a dedicated functional safety subsystem is the Electromagnetic Levitator (EML). This payload for the ISS is planned to be operated on-board starting 2014. The EML is a high-temperature materials processing facility. The dedicated subsystem "Hazard Control Electronics" (HCE) is implemented to ensure compliance to failure tolerance in limiting samples processing parameters to maintain generation of the potentially toxic by-products to safe limits in line with the requirements applied to the payloads by the ISS Program. The objective of this paper is to assess the implementation of the HCE in the EML against criteria for functional safety systems in the IEC-61508 standard and to evaluate commonalities and differences with respect to safety requirements levied on ISS Payloads. An attempt is made to assess a possibility of using commercially available components and systems certified for compliance to industrial functional safety standards in ISS payloads.

Hand-arm vibration in orthopaedic surgery: a neglected risk.

PubMed

Mahmood, F; Ferguson, K B; Clarke, J; Hill, K; Macdonald, E B; Macdonald, D J M

2017-12-30

Hand-arm vibration syndrome is an occupational disease caused by exposure to hand-arm transmitted vibration. The Health and Safety Executive has set limits for vibration exposure, including an exposure action value (EAV), where steps should be taken to reduce exposure, and an exposure limit value (ELV), beyond which vibrating equipment must not be used for the rest of the working day. To measure hand-arm transmitted vibration among orthopaedic surgeons, who routinely use hand-operated saws. We undertook a cadaveric study measuring vibration associated with a tibial cut using battery-operated saws. Three surgeons undertook three tibial cuts each on cadaveric tibiae. Measurements were taken using a frequency-weighted root mean square acceleration, with the vibration total value calculated as the root of the sums squared in each of the three axes. A mean (SD) vibration magnitude of 1 (0.2) m/s2 in the X-axis, 10.3 (1.9) m/s2 in the Y-axis and 4.2 (1.3) m/s2 in the Z-axis was observed. The weighted root mean squared magnitude of vibration was 11.3 (1.7) m/s2. These results suggest an EAV of 23 min and ELV of 1 h 33 min using this equipment. Our results demonstrate that use of a battery-operated sagittal saw can transmit levels of hand-arm vibration approaching the EAV or ELV through prolonged use. Further study is necessary to quantify this risk and establish whether surveillance is necessary for orthopaedic surgeons. © The Author 2017. Published by Oxford University Press on behalf of the Society of Occupational Medicine. All rights reserved. For Permissions, please email: journals.permissions@oup.com

Age-related ventricular-vascular coupling during acute inflammation in humans: Effect of physical activity.

PubMed

Lane, Abbi D; Kappus, Rebecca M; Bunsawat, Kanokwan; Ranadive, Sushant M; Yan, Huimin; Phillips, Shane; Baynard, Tracy; Woods, Jeffrey A; Motl, Robert; Fernhall, Bo

2015-07-01

Aging is commonly accompanied by increased arterial and ventricular stiffness (determined by arterial elastance (Ea) and ventricular elastance (Elv)), augmented ventricular-vascular coupling ratios (Ea/Elv) and systemic inflammation. Acute inflammation may impact ventricular-vascular coupling and predispose older adults to cardiovascular events. However, physically active older adults have more compliant large arteries and left ventricles and lower inflammation than sedentary older adults. We hypothesized that acute inflammation would alter Ea, Elv, and Ea/Elv more in older versus younger adults but that higher levels of physical activity would attenuate inflammation-induced changes. End-systolic and central blood pressures were obtained using applanation tonometry before and at 24 and 48 h post-influenza vaccination in 24 older and 38 younger adults. Ultrasonography was used to measure ventricular volumes and other indices of cardiac performance. Physical activity was measured with accelerometry. Ea and Ea/Elv were maintained (p > 0.05), but Elv was reduced (p < 0.05) 24 h post-inflammation. Other indices of systolic performance were reduced in older but not younger adults; diastolic performance was attenuated in both groups 24 h post-inflammation (p < 0.05 for all). Older, but not younger, adults decreased central pressure during inflammation (p < 0.05). When controlled for age, physical activity was not related to the inflammation-induced changes in elastance (p > 0.05) except in the most active group of seniors (p < 0.05). Aging did not affect the elastance responses but did affect central blood pressure and other ventricular systolic responses to acute inflammation. Aging, not physical activity, appears to modulate cardiovascular responses to acute inflammation, except in the most active older adults. © The European Society of Cardiology 2014 Reprints and permissions: sagepub.co.uk/journalsPermissions.nav.

Long-lasting D-region ionospheric modifications, caused by intense lightning in association with elve and sprite pairs

NASA Astrophysics Data System (ADS)

Haldoupis, Christos; Cohen, Morris; Cotts, Benjamin; Arnone, Enrico; Inan, Umran

2012-08-01

Observations show that intense +CG lightning discharges which trigger both an elve and a sprite are associated with long-lasting conductivity modifications in the upper D-region ionosphere. They are observed as strong perturbations in VLF signals propagating through the disturbed region, manifested as LOng Recovery Early VLF events (LORE), which can last up to 30 minutes. These same ionospheric modifications are also responsible for step-like changes, seen mostly in off-storm VLF transmissions, which offset signal levels even for longer times. The evidence suggests that when a very intense positive cloud to ground lightning stroke leads to an elve and a high altitude sprite, and possibly a sprite halo as well, there is production of long lasting elevations in electron density at VLF reflection heights that cause LOREs and severe effects on VLF propagation. The present results confirm past predictions and postulations that elves may be accompanied by long-lasting electron density perturbations in the lower ionosphere.

Quo Vadis Payload Safety?

NASA Technical Reports Server (NTRS)

Fodroci, Michael P.; Schwartz, MaryBeth

2008-01-01

As we complete the preparations for the fourth Hubble Space Telescope (HST) servicing mission, we note an anniversary approaching: it was 30 years ago in July that the first HST payload safety review panel meeting was held. This, in turn, was just over a year after the very first payload safety review, a Phase 0 review for the Tracking and Data Relay Satellite and its Inertial Upper Stage, held in June of 1977. In adapting a process that had been used in the review and certification of earlier Skylab payloads, National Aeronautics and Space Administration (NASA) engineers sought to preserve the lessons learned in the development of technical payload safety requirements, while creating a new process that would serve the very different needs of the new space shuttle program. Their success in this undertaking is substantiated by the fact that this process and these requirements have proven to be remarkably robust, flexible, and adaptable. Furthermore, the payload safety process has, to date, served us well in the critical mission of safeguarding our astronauts, cosmonauts, and spaceflight participants. Both the technical requirements and their interpretation, as well as the associated process requirements have grown, evolved, been streamlined, and have been adapted to fit multiple programs, including the International Space Station (ISS) program, the Shuttle/Mir program, and most recently the United States Constellation program. From its earliest days, it was anticipated that the payload safety process would be international in scope, and so it has been. European Space Agency (ESA), Japan Aerospace Exploration Agency (JAXA), German Space Agency (DLR), Canadian Space Agency (CSA), Russian Space Agency (RSA), and many additional countries have flown payloads on both the space shuttle and on the ISS. Our close cooperation and long-term working relationships have culminated in the franchising of the payload safety review process itself to our partners in ESA, which in turn will serve as a roadmap for extending the franchise to other Partners.

Ground Processing Affordability for Space Vehicles

NASA Technical Reports Server (NTRS)

Ingalls, John; Scott, Russell

2011-01-01

Launch vehicles and most of their payloads spend the majority of their time on the ground. The cost of ground operations is very high. So, why so often is so little attention given to ground processing during development? The current global space industry and economic environment are driving more need for efficiencies to save time and money. Affordability and sustainability are more important now than ever. We can not continue to treat space vehicles as mere science projects. More RLV's (Reusable Launch Vehicles) are being developed for the gains of reusability which are not available for ELV's (Expendable Launch Vehicles). More human-rated vehicles are being developed, with the retirement of the Space Shuttles, and for a new global space race, yet these cost more than the many unmanned vehicles of today. We can learn many lessons on affordability from RLV's. DFO (Design for Operations) considers ground operations during design, development, and manufacturing-before the first flight. This is often minimized for space vehicles, but is very important. Vehicles are designed for launch and mission operations. You will not be able to do it again if it is too slow or costly to get there. Many times, technology changes faster than space products such that what is launched includes outdated features, thus reducing competitiveness. Ground operations must be considered for the full product Lifecycle, from concept to retirement. Once manufactured, launch vehicles along with their payloads and launch systems require a long path of processing before launch. Initial assembly and testing always discover problems to address. A solid integration program is essential to minimize these impacts, as was seen in the Constellation Ares I-X test rocket. For RLV's, landing/recovery and post-flight turnaround activities are performed. Multi-use vehicles require reconfiguration. MRO (Maintenance, Repair, and Overhaul) must be well-planned--- even for the unplanned problems. Defect limits and standard repairs need to be in-place as well as easily added. Many routine inspections and maintenance can be like an aircraft overhaul. Modifications and technology upgrades should be expected. Another factor affecting ground operations efficiency is trending. It is essential for RLV's, and also useful for ELV's which fly the same or similar models again. Good data analysis of technical and processing performance will determine fixes and improvements needed for safety, design, and future processing. Collecting such data on new or low-frequency vehicles is a challenge. Lessons can be learned from the Space Shuttle, or even the Concorde aircraft. For all of the above topics, efficient business systems must be established for comprehensive program management and good throughput. Drawings, specifications, and manuals for an entire launch vehicle are often in different formats from multiple vendors, plus they have proprietary constraints. Nonetheless, the integration team must ensure that all data needed is compatible and visible to each appropriate team member. Ground processing systems for scheduling, tracking, problem resolution, etc. must be well laid-out. The balance between COTS (commercial off the shelf) and custom software is difficult. Multiple customers, vendors, launch sites, and landing sites add to the complexity of efficient IT (Information Technology) tools.

Safety Concept for a Modern Get Away Special Power Supply

NASA Astrophysics Data System (ADS)

Rieger, T.

2002-01-01

orbiter, providing their own power supply, experiment controls etc. In order to offer a low-cost flight opportunity, the GAS safety review process has been developed, which is not so stringent as the shuttle safety certification process. As a consequence, mainly approved standard components are used in a GAS experiment to ensure safety. This is particularly true for the battery systems of GAS payloads. Many of the modern high power batteries have exhibited hazards. Especially, NASA recommends against the use of Lithium cells in GAS Payloads, which shortens the prospects of extensive experiments due to their power consumption. Considering an experiment with a power consumption of about 100 W, an e.g. standard silver-zinc battery system provides an operating time of typically below 20 h during the complete shuttle mission. Therefore, to take better advantage of the shuttle capabilities, the need for a certified standard Lithium based battery system in the GAS program is given. During the development of the GAS payload G-146, a safe Lithium based battery system has been constructed. This system could be a potential candidate to become such a safe standard component for GAS payloads. Its modular assembly could support various payload designs. The paper states the boundary conditions of the G-146 payload, that led to the design and the safety concept of the Lithium battery system for GAS payloads. The construction is described, considering the influences of safety aspects on the design of the system. The resulting variation possibilities for different GAS- Payloads are described against the background of the retention of the achieved safety level. A further emphasis of the paper is the chosen safety concept during qualification, integration and test of the battery system. Finally, a suggestion for a simple quality assurance concept and an outline of the future applications of the battery system is given.

Radiofrequency Exposures of Workers on Low-Power FM Radio Transmitters.

PubMed

Valic, Blaž; Kos, Bor; Gajšek, Peter

2017-05-01

Low-power radio transmitters are one of the most common radio frequency sources and the exposure limit values (ELVs) for occupational exposure may be exceeded close to them. Therefore, a detailed analysis and assessment of occupational exposure in their vicinity is presented in the paper. For 20 different exposure scenarios, electric field strength and specific absorption rate (SAR) values were computed to determine whether the action levels (ALs) and ELVs of the European directive 2013/35/EU are exceeded for different 500 W radio transmitters. The results show that the ALs are very conservative for such exposure situations. Even when the ALs are greatly exceeded, the SAR values are not necessarily above the limit. However, in some situations, the ELVs were also exceeded. The local 10 g averaged value of the SAR can be exceeded if the worker is grounded (in direct contact with the steel structure), while the whole body ELVs can be exceeded for exposures at distances of <1 m from the transmitting dipole array antennas. © The Author 2017. Published by Oxford University Press on behalf of the British Occupational Hygiene Society.

The D-Region Ledge at Nighttime: Why are Elves Collocated with the OH Meinel Band Airglow Layer?

NASA Astrophysics Data System (ADS)

Wu, Y. J.; Williams, E. R.; Hsu, R. R.

2014-12-01

The Imager of Sprite and Upper Atmosphere Lightning (ISUAL) onboard the Taiwanese satellite Formosat-2 has continuously observed transient luminous events (TLEs) within the +/-60 degree range of latitude for a decade since May 2004. The lightning electromagnetic pulse is responsible for Elves , the dominate TLE type which accounts for approximately 80% of the total TLE count according to the ISUAL global survey. By analyzing the limb-viewed images with a wavelength filter of 622.8-754nm, 72% of elves are found to be 'glued' to the OH Meinel band (~630nm) nightglow layer within its thickness of 8km, with the OH layer normally at an altitude of 87 km (Huang et al., 2010).This collocation of elves and airglow layer is frequently dismissed as coincidence, since the physical mechanisms for the formation of the two optical phenomena are macroscopically quite different. However, a common ingredient in the atmospheric chemistry is monatomic oxygen. O is needed to make O3 and ultimately hydroxyl OH, the main radiative species of the airglow layer. O is also needed to form nitric oxide NO, the species with the lowest known ionization potential (9.26 eV) in the D-region. Thomas (1990) has documented steep increases in O concentration in the 83-85 km altitude range and Hale (1985) has found steep increases in electrical conductivity in the 84-85 km range, both with rocket measurements. A great simplification of the nighttime ionosphere is the presence of a single photon energy—10.2 eV—Lyman-α, originating in monatomic H in the Earth's geocorona. A simple Chapman layer calculation for the altitude of maximum photo-dissociation of O2, using the measured absorption cross-section of O2 at the Lyman-α energy, shows an altitude of maximum O production at 85 km. Elve emission in the nitrogen first positive band is enhanced by the presence of free electrons from ionized NO, but too large a conductivity will lead to the exclusion of the radiation field from the lightning return stroke and suppress the elve emission.. These comparisons of marked changes in key quantities over a narrow range of special altitudes lend support to O being the main player in linking electrical and optical behavior in elve emission.

Elve Doublets: The Ionospheric Fingerprints of Compact Intracloud Discharges

NASA Astrophysics Data System (ADS)

da Silva, C. L.; Marshall, R. A.; Pasko, V. P.

2015-12-01

Compact intracloud discharges (CIDs) persist to date as one of the most mysterious lightning manifestations. CIDs are known to be the strongest natural sources of radio-frequency radiation on Earth. At VHF frequencies, approximately above 30 MHz, their emitted power is ten times stronger than that of other lightning processes. The well-known strength of CIDs in VHF contrasts with the lack of substantial optical measurements. CID's VLF/LF electric field change waveforms resemble one full cycle of a distorted sine function, with the first half-cycle being (a few times) larger-amplitude and shorter-duration than the second. For this reason CIDs have been dubbed narrow bipolar events (NBEs). NBE waveshapes are strikingly similar to the largest initial breakdown pulses (IBPs) that occur during the earlier stages of a conventional lightning flash, called classic IBPs. The similarity between classic IBP and NBE far-field waveforms, combined with the fact that positive-polarity NBEs frequently appear as the first event in an otherwise regular positive intracloud discharge, may be indicative that the source of these two E-field pulse types share the same physical mechanism inside thunderclouds [da Silva and Pasko, JGR, 120, 4989-5009, 2015]. In this presentation, we introduce a novel way to investigate CIDs. We show evidence that CIDs can produce an unique ionospheric signature, named "elve doublets". These signatures are characterized by a pair of elves separated in time by 80-160 microseconds. Our analysis combines fast photometric elve data, equivalent-transmission-line models to describe the dynamics of CID source currents, and FDTD modeling of electromagnetic wave propagation in the Earth-ionosphere waveguide accounting for its nonlinear interaction with the lower ionosphere [Marshall et al., GRL, 42, 2015, doi:10.1002/2015GL064862]. We show that typical (negative-polarity) CID altitudes, between 14-22 km, explain the time delay observed in elve doublets, where the first elve in the doublet is generated by the direct EMP path and the second is generated by its ground reflection. Furthermore, we show that the relative brightness of the first and second elves is likely related to the CID orientation, and angles of 5°-20° with respect to the vertical are consistent with the observed brightness ratios.

GRC Payload Hazard Assessment: Supporting the STS-107 Accident Investigation

NASA Technical Reports Server (NTRS)

Schoren, William R.; Zampino, Edward J.

2004-01-01

A hazard assessment was conducted on the GRC managed payloads in support of a NASA Headquarters Code Q request to examine STS-107 payloads and determine if they were credible contributors to the Columbia accident. This assessment utilized each payload's Final Flight Safety Data Package for hazard identification. An applicability assessment was performed and most of the hazards were eliminated because they dealt with payload operations or crew interactions. A Fault Tree was developed for all the hazards deemed applicable and the safety verification documentation was reviewed for these applicable hazards. At the completion of this hazard assessment, it was concluded that none of the GRC managed payloads were credible contributors to the Columbia accident.

Transportation systems analyses: Volume 1: Executive Summary

NASA Astrophysics Data System (ADS)

1993-05-01

The principal objective of this study is to accomplish a systems engineering assessment of the nation's space transportation infrastructure. This analysis addresses the necessary elements to perform man delivery and return, cargo transfer, cargo delivery, payload servicing, and the exploration of the Moon and Mars. Specific elements analyzed, but not limited to, include the Space Exploration Initiative (SEI), the National Launch System (NLS), the current expendable launch vehicle (ELV) fleet, ground facilities, the Space Station Freedom (SSF), and other civil, military and commercial payloads. The performance of this study entails maintaining a broad perspective on the large number of transportation elements that could potentially comprise the U.S. space infrastructure over the next several decades. To perform this systems evaluation, top-level trade studies are conducted to enhance our understanding of the relationships between elements of the infrastructure. This broad 'infrastructure-level perspective' permits the identification of preferred infrastructures. Sensitivity analyses are performed to assure the credibility and usefulness of study results. This executive summary of the transportation systems analyses (TSM) semi-annual report addresses the SSF logistics resupply. Our analysis parallels the ongoing NASA SSF redesign effort. Therefore, there could be no SSF design to drive our logistics analysis. Consequently, the analysis attempted to bound the reasonable SSF design possibilities (and the subsequent transportation implications). No other strategy really exists until after a final decision is rendered on the SSF configuration.

International Cooperation in the Field of International Space Station (ISS) Payload Safety

NASA Astrophysics Data System (ADS)

Grayson, C.; Sgobba, T.; Larsen, A.; Rose, S.; Heimann, T.; Ciancone, M.; Mulhern, V.

2005-12-01

In the frame of the International Space Station (ISS) Program cooperation, in 1998 the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre- existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and ISS. The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper then presents the background of ISS agreements and international treaties that had to be considered when establishing the ESA PSRP. The paper will expound upon the detailed franchising model, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The paper will then address the resulting ESA PSRP implementation and its success statistics to date. Additionally, the paper presents ongoing developments with the Japan Aerospace Exploration Agency (JAXA). The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.

International Cooperation in the Field of International Space Station (ISS) Payload Safety

NASA Technical Reports Server (NTRS)

Heimann, Timothy; Larsen, Axel M.; Rose, Summer; Sgobba, Tommaso

2005-01-01

In the frame of the International Space Station (ISS) Program cooperation, in 1998, the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre-existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and International Space Station (ISS). The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper 1 then presents the background of ISS agreements and international treaties that had to be taken into account when establishing the ESA PSRP. The detailed franchising model will be expounded upon, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The resulting ESA PSRP implementation and its success statistics to date will then be addressed. Additionally the paper presents the ongoing developments with the Japan Aerospace Exploration Agency. The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.

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.

Comparative study of linkage between environmental policy instruments and technological innovation: Case study on end-of-life vehicles technologies in Japan and EU.

PubMed

Singh, Rajeev Kumar; Yabar, Helmut; Nozaki, Noriko; Niraula, Baburam; Mizunoya, Takeshi

2017-08-01

A growing population and urbanization is a challenge for finite natural resources. Without strict regulation to recycle, recover and reuse resources, waste is discarded with no value. Every year throughout the world, more than twenty-five million vehicles turn into end-of-life vehicles (ELV) and most of their valuable resources end up in landfill sites. This research analyses the effect of regulation on ELV innovation for additional recovery of resources in Japan and EU nations using patent data as a proxy. The analysis determines the statistical difference in patent activity before and after regulations were enacted in the case studies. The relevant data on ELV technologies was gathered for the period 1985-2013. The study suggests that in general environmental regulation in Japan drove innovation and reveals that environmental policy in Japan was more effective in enabling innovation compared to EU nations. Specifically, the results from these developed countries can be used by the rapidly growing developing countries in automobile manufacturing like China for amendment of their ELV regulation accordingly. Copyright © 2017 Elsevier Ltd. All rights reserved.

Mars Sample Return and Flight Test of a Small Bimodal Nuclear Rocket and ISRU Plant

NASA Technical Reports Server (NTRS)

George, Jeffrey A.; Wolinsky, Jason J.; Bilyeu, Michael B.; Scott, John H.

2014-01-01

A combined Nuclear Thermal Rocket (NTR) flight test and Mars Sample Return mission (MSR) is explored as a means of "jump-starting" NTR development. Development of a small-scale engine with relevant fuel and performance could more affordably and quickly "pathfind" the way to larger scale engines. A flight test with subsequent inflight postirradiation evaluation may also be more affordable and expedient compared to ground testing and associated facilities and approvals. Mission trades and a reference scenario based upon a single expendable launch vehicle (ELV) are discussed. A novel "single stack" spacecraft/lander/ascent vehicle concept is described configured around a "top-mounted" downward firing NTR, reusable common tank, and "bottom-mount" bus, payload and landing gear. Requirements for a hypothetical NTR engine are described that would be capable of direct thermal propulsion with either hydrogen or methane propellant, and modest electrical power generation during cruise and Mars surface insitu resource utilization (ISRU) propellant production.

CFD flowfield simulation of Delta Launch Vehicles in a power-on configuration

NASA Technical Reports Server (NTRS)

Pavish, D. L.; Gielda, T. P.; Soni, B. K.; Deese, J. E.; Agarwal, R. K.

1993-01-01

This paper summarizes recent work at McDonnell Douglas Aerospace (MDA) to develop and validate computational fluid dynamic (CFD) simulations of under expanded rocket plume external flowfields for multibody expendable launch vehicles (ELVs). Multi engine reacting gas flowfield predictions of ELV base pressures are needed to define vehicle base drag and base heating rates for sizing external nozzle and base region insulation thicknesses. Previous ELV design programs used expensive multibody power-on wind tunnel tests that employed chamber/nozzle injected high pressure cold or hot-air. Base heating and pressure measurements were belatedly made during the first flights of past ELV's to correct estimates from semi-empirical engineering models or scale model tests. Presently, CFD methods for use in ELV design are being jointly developed at the Space Transportation Division (MDA-STD) and New Aircraft Missiles Division (MDA-NAMD). An explicit three dimensional, zonal, finite-volume, full Navier-Stokes (FNS) solver with finite rate hydrocarbon/air and aluminum combustion kinetics was developed to accurately compute ELV power-on flowfields. Mississippi State University's GENIE++ general purpose interactive grid generation code was chosen to create zonal, finite volume viscous grids. Axisymmetric, time dependent, turbulent CFD simulations of a Delta DSV-2A vehicle with a MB-3 liquid main engine burning RJ-1/LOX were first completed. Hydrocarbon chemical kinetics and a k-epsilon turbulence model were employed and predictions were validated with flight measurements of base pressure and temperature. Zonal internal/external grids were created for a Delta DSV-2C vehicle with a MB-3 and three Castor-1 solid motors burning and a Delta-2 with an RS-27 main engine (LOX/RP-1) and 9 GEM's attached/6 burning. Cold air, time dependent FNS calculations were performed for DSV-2C during 1992. Single phase simulations that employ finite rate hydrocarbon and aluminum (solid fuel) combustion chemistry are currently in progress. Reliable and efficient Eulerian algorithms are needed to model two phase (solid-gas) momentum and energy transfer mechanisms for solid motor fuel combustion products.

CFD flowfield simulation of Delta Launch Vehicles in a power-on configuration

NASA Astrophysics Data System (ADS)

Pavish, D. L.; Gielda, T. P.; Soni, B. K.; Deese, J. E.; Agarwal, R. K.

1993-07-01

This paper summarizes recent work at McDonnell Douglas Aerospace (MDA) to develop and validate computational fluid dynamic (CFD) simulations of under expanded rocket plume external flowfields for multibody expendable launch vehicles (ELVs). Multi engine reacting gas flowfield predictions of ELV base pressures are needed to define vehicle base drag and base heating rates for sizing external nozzle and base region insulation thicknesses. Previous ELV design programs used expensive multibody power-on wind tunnel tests that employed chamber/nozzle injected high pressure cold or hot-air. Base heating and pressure measurements were belatedly made during the first flights of past ELV's to correct estimates from semi-empirical engineering models or scale model tests. Presently, CFD methods for use in ELV design are being jointly developed at the Space Transportation Division (MDA-STD) and New Aircraft Missiles Division (MDA-NAMD). An explicit three dimensional, zonal, finite-volume, full Navier-Stokes (FNS) solver with finite rate hydrocarbon/air and aluminum combustion kinetics was developed to accurately compute ELV power-on flowfields. Mississippi State University's GENIE++ general purpose interactive grid generation code was chosen to create zonal, finite volume viscous grids. Axisymmetric, time dependent, turbulent CFD simulations of a Delta DSV-2A vehicle with a MB-3 liquid main engine burning RJ-1/LOX were first completed. Hydrocarbon chemical kinetics and a k-epsilon turbulence model were employed and predictions were validated with flight measurements of base pressure and temperature. Zonal internal/external grids were created for a Delta DSV-2C vehicle with a MB-3 and three Castor-1 solid motors burning and a Delta-2 with an RS-27 main engine (LOX/RP-1) and 9 GEM's attached/6 burning. Cold air, time dependent FNS calculations were performed for DSV-2C during 1992. Single phase simulations that employ finite rate hydrocarbon and aluminum (solid fuel) combustion chemistry are currently in progress. Reliable and efficient Eulerian algorithms are needed to model two phase (solid-gas) momentum and energy transfer mechanisms for solid motor fuel combustion products.

Payload Safety: Risk and Characteristic-Based Control of Engineered Nanomaterials

NASA Astrophysics Data System (ADS)

Abou, Seraphin Chally; Saad, Maarouf

2013-09-01

In the last decade progress has been made to assist organizations that are developing payloads intended for flight on the International Space Station (ISS) and/or Space Shuttle. Collaboration programs for comprehensive risk assessment have been initiated between the U.S. and the European Union to generate requirements and data needed to comply with payloads safety and to perform risk assessment and controls guidance. Yet, substantial research gaps remain, as do challenges in the translation of these research findings to control for exposure to nanoscale material payloads, and the health effects. Since nanomaterial structures are different from traditional molecules, some standard material properties can change at size of 50nm or less. Changes in material properties at this scale challenge our understanding of hazards posed by nanomaterial payloads in the ISS realistic exposure conditions, and our ability to anticipate, evaluate, and control potential health issues, and safety. The research question addressed in this framework is: what kind of descriptors can be developed for nanomaterial payloads risks assessment? Methods proposed incorporate elements of characteristic- based risk an alysis: (1) to enable characterization of anthropogenic nanomaterials which can result in incidental from natural nanoparticles; and (2) to better understand safety attributes in terms of human health impacts from exposure to varying types of engineered nanomaterials.

Sex differences in ventricular-vascular coupling following endurance training.

PubMed

Lane, A D; Yan, H; Ranadive, S M; Kappus, R M; Sun, P; Cook, M D; Harvey, I; Woods, J; Wilund, K; Fernhall, B

2014-12-01

Ventricular and vascular coupling is defined as the ratio of arterial elastance (Ea) to ventricular elastance (Elv) and describes the interaction between the heart and arterial system. There are sex differences in both arterial and ventricular function in response to both acute exercise and aerobic exercise training. To examine the effects of aerobic exercise training on elastances and the coupling ratio in young adult men and women. We hypothesized a reduction in the coupling ratio in both sexes due to a decrease in Ea that would be more pronounced in men and an increase in Elv that would be larger in women. Fifty-three healthy, young adults completed the study. Central pulse wave velocity and heart volumes were measured before and after an 8-week aerobic training intervention. Elastances were calculated as Ea = end-systolic pressure/stroke volume and Elv = end-systolic pressure/end-systolic volume and indexed to body surface area. After the intervention, women augmented indexed and un-indexed Elv from 2.09 ± 0.61 to 2.52 ± 0.80 mmHg/ml, p < 0.05, and reduced the coupling ratio from 0.72 ± 18 to 0.62 ± 15, p < 0.05, while men maintained their pre-training ratio (from 0.66 ± 0.20 to 0.74 ± 0.21, p > 0.05). Women also reduced end-systolic pressure (from 91 ± 10 to 87 ± 10 mmHg), and both groups reduced central pulse wave velocity (from 6.0 ± 1.0 to 5.6 ± 0.6 m/s, p < 0.05). We conclude that after 8 weeks of aerobic training, only women reduced their coupling ratio due to an increase in Elv. This suggests that aerobic exercise training elicits sex-dependent changes in the coupling ratio in young, healthy individuals.

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.

The influence of joint technologies on ELV recyclability.

PubMed

Soo, Vi Kie; Compston, Paul; Doolan, Matthew

2017-10-01

Stricter vehicle emission legislation has led to the increasing use of lightweight materials and multi-material concepts to reduce the vehicle mass. To account for the complexity of multi-material vehicle designs, the choice of joining techniques used is becoming more diverse. Moreover, the different material combinations, and their respective joining methods play an important role in determining the potential of full material separation in a closed-loop system. This paper evaluates the types of joining technologies used in the automotive industry, and identifies those that hinder the sorting of ELV materials. The study is based on an industrial shredding trial of car doors. Observations from the case study showed that steel screws and bolts are increasingly used to combine different material types and are less likely to be perfectly liberated during the shredding process. The characteristics of joints that lead to impurities and valuable material losses, such as joint strength, material type, size, diameter, location, and protrusion level, can influence the material liberation in the current sorting practices and thus, lead to ELV waste minimisation. Additionally, the liberation of joints is also affected by the density and thickness of materials being joined. Correlation analyses are carried out to further support the influence of mechanical screws and bolts on material separation efficiencies. The observations are representative of the initial phases of current global ELV sorting practices. Copyright © 2017 Elsevier Ltd. All rights reserved.

Auto shredder residue recycling: Mechanical separation and pyrolysis.

PubMed

Santini, Alessandro; Passarini, Fabrizio; Vassura, Ivano; Serrano, David; Dufour, Javier; Morselli, Luciano

2012-05-01

Directive 2000/53/EC sets a goal of 85% material recycling from end-of-life vehicles (ELVs) by the end of 2015. The current ELV recycling rate is around 80%, while the remaining waste is called automotive shredder residue (ASR), or car fluff. In Europe, this is mainly landfilled because it is extremely heterogeneous and often polluted with car fluids. Despite technical difficulties, in the coming years it will be necessary to recover materials from car fluff in order to meet the ELV Directive requirement. This study deals with ASR pretreatment and pyrolysis, and aims to determine whether the ELV material recycling target may be achieved by car fluff mechanical separation followed by pyrolysis with a bench scale reactor. Results show that flotation followed by pyrolysis of the light, organic fraction may be a suitable ASR recycling technique if the oil can be further refined and used as a chemical. Moreover, metals are liberated during thermal cracking and can be easily separated from the pyrolysis char, amounting to roughly 5% in mass. Lastly, pyrolysis can be a good starting point from a "waste-to-chemicals" perspective, but further research should be done with a focus on oil and gas refining, in order both to make products suitable for the chemical industry and to render the whole recycling process economically feasible. Copyright © 2011 Elsevier Ltd. All rights reserved.

The Operational Role of the Belgian User Support and Operations Centre for the Atmosphere-Space Interactions Monitor (ASIM) on-board the International Space Station.

NASA Astrophysics Data System (ADS)

Muller, C.; Moreau, D., Sr.; Pandey, P. K.; Crosby, N. B.

2014-12-01

The Belgian User Support and Operations Centre (B.USOC) is an operational centre managing technological and scientific payloads on the International Space Station (ISS). B.USOC is the Facility Responsible Centre (FRC) for the European Space Agency's (ESA) Atmosphere-Space Interactions Monitor (ASIM) payload and also manages the Scientific Mission Centre of the Centre National d'Etudes Spatiales (CNES) PICARD satellite that monitors solar activity, among various other space missions. In this respect, B.USOC is ideally positioned to manage possible synergies between ASIM, the satellite TARANIS (Tool for the Analysis of RAdiation from lightNIng and Sprites), other space missions and ground-based networks. The ASIM mission (Neubert, 2009) consists of a package of two nadir instruments: one for the visible spectrum and another for X-ray and gamma-ray frequencies. In the normal operating mode "trigger mode" both instruments continuously measure, but, do not record data below certain thresholds. Another mode is a "timed mode", where, during a certain time the observations are recorded even in the absence of triggers. The "timed mode" demands a lot of flexibility from both scientific teams and B.USOC, as, ASIM's main targets of investigation (sprites and elves) are related to intense thunderstorms and thus, require reliable meteorological forecasts in the entire range of ISS latitudes. Moreover, ASIM is sensitive to a large number of phenomena of which most have a direct relationship with solar activity and therefore would probably need support from the ESA SSA (Space Situational Awareness) Space Weather Coordination Centre (SSCC) that shares the same campus with B.USOC. Local cooperation between the two centres, together with other space payloads such as TARANIS and ground-based networks will greatly optimize ASIM payload operations as well as scientific return. Neubert, T., and the ASIM Team, ASIM - an Instrument Suite for the International Space Station, Corte Workshop 2008, Coupling of Thunderstorms and Lightning Discharges to Near-Earth, Corsica, 2008, edited by N. B. Crosby et al, American Institute of Physics, 978-0-7354-0657-5/09/, 2009.

Data Requirement (DR) MA-03: Payload missions integration. [Spacelab payloads

NASA Technical Reports Server (NTRS)

1985-01-01

Project management and payload integration requirements definition activities are reported. Mission peculiar equipment; systems integration; ground operations analysis and requirement definition; safety and quality assurance; and support systems development are examined for payloads planned for the following missions: EOM-1; SL-2; Sl-3 Astro-1; MSL-2; EASE/ACCESS; MPESS; and the middeck ADSF flight.

Assessment of mixed fleet potential for space station launch and assembly

NASA Technical Reports Server (NTRS)

Deryder, L. J. (Editor)

1987-01-01

Reductions in expected STS flight rates of the Space Shuttle since the 51-L accident raise concerns about the ability of available launch capacity to meet both payload-to-orbit and crew rotation requirements for the Space Station. In addition, it is believed that some phases of Station build-up could be expedited using unmanned launch systems with significantly greater lift capacity than the STS. Examined is the potential use of expendable launch vehicles (ELVs), yet-to-be-developed unmanned shuttle-derived vehicles (SDVs), and international launch vehicles for meeting overall launch requirements to meet Space Station program objectives as defined by the 1986 Critical Evaluation Task Force (CETF). The study concludes that use of non-STS transportation can help meet several important program objectives as well as reduce the total number of STS flights. It also finds, however, that reduction of Space Station-dedicated STS flights below 8 per year forces a reduction in Station crew size assuming the CETF 90 day crew stay time baseline and seriously impairs scientific utilization of the Station.

Evaluation philosophy for shuttle launched payloads

NASA Technical Reports Server (NTRS)

Heuser, R. E.

1975-01-01

Some approaches to space-shuttle payload evaluation are examined. Issues considered include subsystem replacement in low-cost modular spacecraft (LCMS), validation of spacelab payloads, the use of standard components in shuttle-era spacecraft, effects of shuttle-induced environments on payloads, and crew safety. The LCMS is described, and goals are discussed for its evaluation program. Concepts regarding how the evaluation should proceed are considered.

Elves and associated electron density changes due to cloud-to-ground and in-cloud lightning discharges

NASA Astrophysics Data System (ADS)

Marshall, R. A.; Inan, U. S.; Glukhov, V. S.

2010-04-01

A 3-D finite difference time domain model is used to simulate the lightning electromagnetic pulse (EMP) and its interaction with the lower ionosphere. Results agree with the frequently observed, doughnut-shaped optical signature of elves but show that the structure exhibits asymmetry due to the presence of Earth's ambient magnetic field. Furthermore, in-cloud (horizontal) lightning channels produce observable optical emissions without the doughnut shape and, in fact, produce a much stronger optical output for the same channel current. Electron density perturbations associated with elves are also calculated, with contributions from attachment and ionization. Results presented as a function of parameters such as magnetic field direction, dipole current orientation, altitude and amplitude, and ambient ionospheric density profile demonstrate the highly nonlinear nature of the EMP-ionosphere interaction. Ionospheric effects of a sequence of in-cloud discharges are calculated, simulating a burst of in-cloud lightning activity and resulting in large density changes in the overlying ionosphere.

Manned space flight nuclear system safety. Voluem 5: Nuclear system safety guidelines. Part 2: Space shuttle/nuclear payloads safety

NASA Technical Reports Server (NTRS)

1972-01-01

The design and operations guidelines and requirements developed in the study of space shuttle nuclear system transportation are presented. Guidelines and requirements are presented for the shuttle, nuclear payloads (reactor, isotope-Brayton and small isotope sources), ground support systems and facilities. Cross indices and references are provided which relate guidelines to each other, and to substantiating data in other volumes. The guidelines are intended for the implementation of nuclear safety related design and operational considerations in future space programs.

Boiling eXperiment Facility (BXF) Fluid Toxicity Technical Interchange Meeting (TIM) with the Payload Safety Review Panel (PSRP)

NASA Technical Reports Server (NTRS)

Sheredy, William A.

2012-01-01

A Technical Interchange meeting was held between the payload developers for the Boiling eXperiment Facility (BXF) and the NASA Safety Review Panel concerning operational anomaly that resulted in overheating one of the fluid heaters, shorted a 24VDC power supply and generated Perfluoroisobutylene (PFiB) from Perfluorohexane.

Building on the Past - Looking to the Future: A Focus on Payload Safety

NASA Technical Reports Server (NTRS)

Nash, Sally K.; Rehm, Raymond B.; Samtoagp. Darren M.; Wong, Teresa K.; Wolf, Scott L.

2008-01-01

The history of the space industry stretches far and above lunar landings to the construction of the International Space Station. For years, humans have sought to understand the nature of the universe. As society grows in knowledge and curiosity of space, the focus of maintaining the safety of the crew and vehicle habitability is of utmost importance to the National Aeronautics and Space Administration (NASA) community. Through the years, Payload Safety has developed not only as a Panel, but also as part of the NASA community, striving to enhance the efficiency and understanding of how business should be conducted as more International Partners become involved. This is the first in a series of papers and presentations in what is hoped to be an annual update that provides continuous challenges and lessons learned in the areas of communication, safety requirements and processes and other areas which have been vital to the Payload Safety Review Panel (PSRP).

Respiratory effort correction strategies to improve the reproducibility of lung expansion measurements

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

Du, Kaifang; Reinhardt, Joseph M.; Christensen, Gary E.

2013-12-15

Purpose: Four-dimensional computed tomography (4DCT) can be used to make measurements of pulmonary function longitudinally. The sensitivity of such measurements to identify change depends on measurement uncertainty. Previously, intrasubject reproducibility of Jacobian-based measures of lung tissue expansion was studied in two repeat prior-RT 4DCT human acquisitions. Difference in respiratory effort such as breathing amplitude and frequency may affect longitudinal function assessment. In this study, the authors present normalization schemes that correct ventilation images for variations in respiratory effort and assess the reproducibility improvement after effort correction.Methods: Repeat 4DCT image data acquired within a short time interval from 24 patients priormore » to radiation therapy (RT) were used for this analysis. Using a tissue volume preserving deformable image registration algorithm, Jacobian ventilation maps in two scanning sessions were computed and compared on the same coordinate for reproducibility analysis. In addition to computing the ventilation maps from end expiration to end inspiration, the authors investigated the effort normalization strategies using other intermediated inspiration phases upon the principles of equivalent tidal volume (ETV) and equivalent lung volume (ELV). Scatter plots and mean square error of the repeat ventilation maps and the Jacobian ratio map were generated for four conditions: no effort correction, global normalization, ETV, and ELV. In addition, gamma pass rate was calculated from a modified gamma index evaluation between two ventilation maps, using acceptance criterions of 2 mm distance-to-agreement and 5% ventilation difference.Results: The pattern of regional pulmonary ventilation changes as lung volume changes. All effort correction strategies improved reproducibility when changes in respiratory effort were greater than 150 cc (p < 0.005 with regard to the gamma pass rate). Improvement of reproducibility was correlated with respiratory effort difference (R = 0.744 for ELV in the cohort with tidal volume difference greater than 100 cc). In general for all subjects, global normalization, ETV and ELV significantly improved reproducibility compared to no effort correction (p = 0.009, 0.002, 0.005 respectively). When tidal volume difference was small (less than 100 cc), none of the three effort correction strategies improved reproducibility significantly (p = 0.52, 0.46, 0.46 respectively). For the cohort (N = 13) with tidal volume difference greater than 100 cc, the average gamma pass rate improves from 57.3% before correction to 66.3% after global normalization, and 76.3% after ELV. ELV was found to be significantly better than global normalization (p = 0.04 for all subjects, and p = 0.003 for the cohort with tidal volume difference greater than 100 cc).Conclusions: All effort correction strategies improve the reproducibility of the authors' pulmonary ventilation measures, and the improvement of reproducibility is highly correlated with the changes in respiratory effort. ELV gives better results as effort difference increase, followed by ETV, then global. However, based on the spatial and temporal heterogeneity in the lung expansion rate, a single scaling factor (e.g., global normalization) appears to be less accurate to correct the ventilation map when changes in respiratory effort are large.« less

Strategies for the enhancement of automobile shredder residues (ASRs) recycling: results and cost assessment.

PubMed

Ruffino, Barbara; Fiore, Silvia; Zanetti, Maria Chiara

2014-01-01

With reference to the European regulation about the management of End-of-Life Vehicles (ELVs), Directive 2000/53/EC imposes the achievement of a recycling target of 85%, and 95% of total recovery by 2015. Over the last few years many efforts have been made to find solutions to properly manage the waste coming from ELVs with the aim of complying with the targets fixed by the Directive. This paper focuses on the economical evaluation of a treatment process, that includes physical (size and density), magnetic and electrical separations, performed on the light fraction of the automobile shredder residue (ASR) with the aim of reducing the amount of waste to dispose of in a landfill and enhancing the recovery of valuable fractions as stated by the EU Directive. The afore mentioned process is able to enhance the recovery of ferrous and non-ferrous metals of an amount equal to about 1% b.w. (by weight) of the ELV weight, and to separate a high energetic-content product suitable for thermal valorization for an amount close to (but not higher than) 10% b.w. of the ELV weight. The results of the economical assessment led to annual operating costs of the treatment ranging from 300,000 €/y to 350,000 €/y. Since the considered plant treats about 13,500 metrictons of ASR per year, this would correspond to an operating cost of approximately 20-25 €/t. Taking into account the amount and the selling price of the scrap iron and of the non magnetic metal recovered by the process, thus leading to a gain of about 30 €/t per ton of light ASR treated, the cost of the recovery process is balanced by the profit from the selling of the recovered metals. On the other hand, the proposed treatment is able to achieve the fulfillment of the targets stated by Directive 2000/53/EC concerning thermal valorization and reduce the amount of waste generated from ELV shredding to landfill. Copyright © 2013 Elsevier Ltd. All rights reserved.

Safety in earth orbit study. Volume 1: Technical summary

NASA Technical Reports Server (NTRS)

1972-01-01

A summary of the technical results and conclusions is presented of the hazards analyses of earth orbital operations in conjunction with the space shuttle program. The space shuttle orbiter and a variety of manned and unmanned payloads delivered to orbit by the shuttle are considered. The specific safety areas examined are hazardous payloads, docking, on-orbit survivability, tumbling spacecraft, and escape and rescue.

Orbital spacecraft consumables resupply

NASA Technical Reports Server (NTRS)

Dominick, Sam M.; Eberhardt, Ralph N.; Tracey, Thomas R.

1988-01-01

The capability to replenish spacecraft, satellites, and laboratories on-orbit with consumable fluids provides significant increases in their cost and operational effectiveness. Tanker systems to perform on-orbit fluid resupply must be flexible enough to operate from the Space Transportation System (STS), Space Station, or the Orbital Maneuvering Vehicle (OMV), and to accommodate launch from both the Shuttle and Expendable Launch Vehicles (ELV's). Resupply systems for storable monopropellant hydrazine and bipropellants, and water have been developed. These studies have concluded that designing tankers capable of launch on both the Shuttle and ELV's was feasible and desirable. Design modifications and interfaces for an ELV launch of the tanker systems were identified. Additionally, it was determined that modularization of the tanker subsystems was necessary to provide the most versatile tanker and most efficient approach for use at the Space Station. The need to develop an automatic umbilical mating mechanism, capable of performing both docking and coupler mating functions was identified. Preliminary requirements for such a mechanism were defined. The study resulted in a modular tanker capable of resupplying monopropellants, bipropellants, and water with a single design.

Atmospheric, Magnetospheric and plasmas in Space (AMPS) spacelab payload definition study; Volume 4: Part 3, Labcraft instrument systems general specification

NASA Technical Reports Server (NTRS)

Keeley, J. T.

1976-01-01

Guidelines and general requirements applicable to the development of instrument flight hardware intended for use on the GSFC Shuttle Scientific Payloads Program are given. Criteria, guidelines, and an organized approach to specifying the appropriate level of requirements for each instrument in order to permit its development at minimum cost while still assuring crew safety, are included. It is recognized that the instruments for these payloads will encompass wide ranges of complexity, cost, development risk, and safety hazards. The flexibility required to adapt the controls, documentation, and verification requirements in accord with the specific instrument is provided.

Rocket propulsion hazard summary: Safety classification, handling experience and application to space shuttle payload

NASA Technical Reports Server (NTRS)

Pennington, D. F.; Man, T.; Persons, B.

1977-01-01

The DOT classification for transportation, the military classification for quantity distance, and hazard compatibility grouping used to regulate the transportation and storage of explosives are presented along with a discussion of tests used in determining sensitivity of propellants to an impact/shock environment in the absence of a large explosive donor. The safety procedures and requirements of a Scout launch vehicle, Western and Eastern Test Range, and the Minuteman, Delta, and Poseidon programs are reviewed and summarized. Requirements of the space transportation system safety program include safety reviews from the subsystem level to the completed payload. The Scout safety procedures will satisfy a portion of these requirements but additional procedures need to be implemented to comply with the safety requirements for Shuttle operation from the Eastern Test Range.

Space Transportation Infrastructure Supported By Propellant Depots

NASA Technical Reports Server (NTRS)

Smitherman, David; Woodcock, Gordon

2012-01-01

A space transportation infrastructure is described that utilizes propellant depot servicing platforms to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicle (ELV) systems such as the Delta IV Heavy, Atlas V, and Falcon 9, for all crew, cargo, and propellant launches to orbit. Propellant launches are made to Low-Earth-Orbit (LEO) Depot and an Earth-Moon Lagrange Point 1 (L1) Depot to support a new reusable in-space transportation vehicles. The LEO Depot supports missions to Geosynchronous Earth Orbit (GEO) for satellite servicing and to L1 for L1 Depot missions. The L1 Depot supports Lunar, Earth-Sun L2 (ESL2), Asteroid and Mars Missions. New vehicle design concepts are presented that can be launched on current 5 meter diameter ELV systems. These new reusable vehicle concepts include a Crew Transfer Vehicle (CTV) for crew transportation between the LEO Depot, L1 Depot and missions beyond L1; a new reusable lunar lander for crew transportation between the L1 Depot and the lunar surface; and Mars orbital Depot are based on International Space Station (ISS) heritage hardware. Data provided includes the number of launches required for each mission utilizing current ELV systems (Delta IV Heavy or equivalent) and the approximate vehicle masses and propellant requirements. Also included is a discussion on affordability with ideas on technologies that could reduce the number of launches required and thoughts on how this infrastructure include competitive bidding for ELV flights and propellant services, developments of new reusable in-space vehicles and development of a multiuse infrastructure that can support many government and commercial missions simultaneously.

A Human Factors Framework for Payload Display Design

NASA Technical Reports Server (NTRS)

Dunn, Mariea C.; Hutchinson, Sonya L.

1998-01-01

During missions to space, one charge of the astronaut crew is to conduct research experiments. These experiments, referred to as payloads, typically are controlled by computers. Crewmembers interact with payload computers by using visual interfaces or displays. To enhance the safety, productivity, and efficiency of crewmember interaction with payload displays, particular attention must be paid to the usability of these displays. Enhancing display usability requires adoption of a design process that incorporates human factors engineering principles at each stage. This paper presents a proposed framework for incorporating human factors engineering principles into the payload display design process.

Safety in earth orbit study. Volume 2: Analysis of hazardous payloads, docking, on-board survivability

NASA Technical Reports Server (NTRS)

1972-01-01

Detailed and supporting analyses are presented of the hazardous payloads, docking, and on-board survivability aspects connected with earth orbital operations of the space shuttle program. The hazards resulting from delivery, deployment, and retrieval of hazardous payloads, and from handling and transport of cargo between orbiter, sortie modules, and space station are identified and analyzed. The safety aspects of shuttle orbiter to modular space station docking includes docking for assembly of space station, normal resupply docking, and emergency docking. Personnel traffic patterns, escape routes, and on-board survivability are analyzed for orbiter with crew and passenger, sortie modules, and modular space station, under normal, emergency, and EVA and IVA operations.

NASA study backs SSTO, urges shuttle phaseout

NASA Astrophysics Data System (ADS)

Asker, James R.

1994-03-01

A brief discusion of a Congressionally ordered NASA study on how to meet future US Government space launch needs is presented. Three options were examined: (1) improvement ofthe Space Shuttle; (2) development of expendable launch vehicles (ELVs); and (3) development of a single-stage-to-orbit (SSTO), manned vehicle that is reusable with advanced technology. After examining the three options, it was determined that the most economical approach to space access through the year 2030 would be to develop the SSTO vehicle and phase out Space Shuttle operations within 15 years and ELVs within 20 years. Other aspects of the study's findings are briefly covered.

Review of Italian experience on automotive shredder residue characterization and management.

PubMed

Cossu, R; Fiore, S; Lai, T; Luciano, A; Mancini, G; Ruffino, B; Viotti, P; Zanetti, M C

2014-10-01

Automotive Shredder Residue (ASR) is a special waste that can be classified as either hazardous or non hazardous depending on the amount of hazardous substances and on the features of leachate gathered from EN12457/2 test. However both the strict regulation concerning landfills and the EU targets related to End-of-Life Vehicles (ELVs) recovery and recycling rate to achieve by 2015 (Directive 2000/53/EC), will limit current landfilling practice and will impose an increased efficiency of ELVs valorization. The present paper considers ELVs context in Italy, taking into account ASRs physical-chemical features and current processing practice, focusing on the enhancement of secondary materials recovery. The application in waste-to-energy plants, cement kilns or metallurgical processes is also analyzed, with a particular attention to the possible connected environmental impacts. Pyrolysis and gasification are considered as emerging technologies although the only use of ASR is debatable; its mixing with other waste streams is gradually being applied in commercial processes. The environmental impacts of the processes are acceptable, but more supporting data are needed and the advantage over (co-)incineration remains to be proven. Copyright © 2013 Elsevier Ltd. All rights reserved.

Automobile Shredder Residues in Italy: characterization and valorization opportunities.

PubMed

Fiore, S; Ruffino, B; Zanetti, M C

2012-08-01

At the moment Automobile Shredder Residue (ASR) is usually landfilled worldwide, but European draft Directive 2000/53/CE forces the development of alternative solutions, stating the 95%-wt recovery of an End of Life Vehicle (ELV) weight to be fulfilled by 2015. This work describes two industrial tests, each involving 250-300 t of ELVs, in which different pre-shredding operations were performed. The produced ASR materials underwent an extended characterization and some post-shredding processes, consisting of dimensional, magnetic, electrostatic and densimetric separation phases, were tested on laboratory scale, having as main purpose the enhancement of ASR recovery/recycling and the minimization of the landfilled fraction. The gathered results show that accurate depollution and dismantling operations are mandatory to obtain a high quality ASR material which may be recycled/recovered and partially landfilled according to the actual European Union regulations, with particular concern for Lower Heating Value (LHV), heavy metals content and Dissolved Organic Carbon (DOC) as critical parameters. Moreover post-shredding technical solutions foreseeing minimum economic and engineering efforts, therefore realizable in common European ELVs shredding plants, may lead to multi-purposed (material recovery and thermal valorization) opportunities for ASR reuse/recovery. Copyright © 2012 Elsevier Ltd. All rights reserved.

Influence of Pentacene Interface Layer in ITO/α-NPD/Alq3/Al Organic Light Emitting Diodes by Time-Resolved Electric-Field-Induced Optical Second-Harmonic Generation Measurement.

PubMed

Oda, Yoshiaki; Sadakata, Atsuo; Taguchi, Dai; Manaka, Takaaki; Iwamoto, Mitsumasa

2016-04-01

By using I-V, EL-V, displacement current measurement (DCM) and time-resolved electric-field-induced optical second-harmonic generation (TR-EFISHG) measurement, we studied the influence of interface pentacene layer inserted between ITO and a-NPD layers in ITO/α-NPD/Alq3/Al OLEDs. All experiments were carried out for the OLEDs with and without a pentacene interface layer. The I-V and EL-V measurements showed the decrease of operating voltage of EL, the DCM showed the lowering of inception voltage of carrier injection by inserting a pentacene interface layer. The TR-EFISHG measurement showed the faster accumulation of holes at the interface between the a-NPD and Alq3 layers, which resulted in the relaxation of electric field of a-NPD layer accomplished by the increase of the conductivity and the increase of the electric field in the Alq3 layer. We conclude that TR-EFISHG measurement is helpful for understanding I-V and EL-V characteristics, and can be combined with other methods to give significant information which are impacted by the interface layer.

14 CFR 1214.608 - Safety requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Space Shuttle Flights § 1214.608 Safety requirements. The contents of OFK's and PPK's must meet the requirements set forth in NASA Handbook 1700.7, “Safety Policy and Requirements for Payloads Using the Space...

14 CFR 1214.608 - Safety requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Space Shuttle Flights § 1214.608 Safety requirements. The contents of OFK's and PPK's must meet the requirements set forth in NASA Handbook 1700.7, “Safety Policy and Requirements for Payloads Using the Space...

Streamlining Payload Integration

NASA Technical Reports Server (NTRS)

Lufkin, Susan N.

2010-01-01

Payload integration onto space transport vehicles and the International Space Station (ISS) is a complex process. Yet, cargo transport is the sole reason for any space mission, be it for ferrying humans, science, or hardware. As the largest such effort in history, the ISS offers a wide variety of payload experience. However, for any payload to reach the Space Station under the current process, Payload Developers face a list of daunting tasks that go well beyond just designing the payload to the constraints of the transport vehicle and its stowage topology. Payload customers are required to prove their payload s functionality, structural integrity, and safe integration - including under less than nominal situations. They must also plan for or provide training, procedures, hardware labeling, ground support, and communications. In addition, they must deal with negotiating shared consumables, integrating software, obtaining video, and coordinating the return of data and hardware. All the while, they must meet export laws, launch schedules, budget limits, and the consensus of more than 12 panel and board reviews. Despite the cost and infrastructure overhead, payload proposals have increased. Just in the span from FY08 to FY09, the NASA Payload Space Station Support Office budget rose from $78M to $96M in attempt to manage the growing manifest, but the potential number of payloads still exceeds available Payload Integration Management manpower. The growth has also increased management difficulties due to the fact that payloads are more frequently added to a flight schedule late in the flow. The current standard ISS template for payload integration from concept to payload turn-over is 36 months, or 18 months if the payload already has a preliminary design. Customers are increasingly requiring a turn-around of 3 to 6-months to meet market needs. The following paper suggests options for streamlining the current payload integration process in order to meet customer schedule needs and reduce costs for both the integration support teams and the developers, without reducing quality or compromising safety. Issues for the key integration areas of planning, training, verification, and safety are presented in a Root-Cause Analysis study, with plausible solutions provided that involve technology and tools already available to the ISS community. Although based upon the ISS process, the payload integration techniques outlined herein also offer an integration template for any space transport endeavor.

14 CFR § 1214.608 - Safety requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Aboard Space Shuttle Flights § 1214.608 Safety requirements. The contents of OFK's and PPK's must meet the requirements set forth in NASA Handbook 1700.7, “Safety Policy and Requirements for Payloads Using...

The 15th Aerospace Mechanisms Symposium

NASA Technical Reports Server (NTRS)

1981-01-01

Technological areas covered include: aerospace propulsion; aerodynamic devices; crew safety; space vehicle control; spacecraft deployment, positioning, and pointing; deployable antennas/reflectors; and large space structures. Devices for payload deployment, payload retention, and crew extravehicular activities on the space shuttle orbiter are also described.

KSC-06pd0857

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads nears the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

KSC-06pd0858

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads nears the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

KSC-06pd0856

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads is lifted toward the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

Designing an Alternate Mission Operations Control Room

NASA Technical Reports Server (NTRS)

Montgomery, Patty; Reeves, A. Scott

2014-01-01

The Huntsville Operations Support Center (HOSC) is a multi-project facility that is responsible for 24x7 real-time International Space Station (ISS) payload operations management, integration, and control and has the capability to support small satellite projects and will provide real-time support for SLS launches. The HOSC is a service-oriented/ highly available operations center for ISS payloads-directly supporting science teams across the world responsible for the payloads. The HOSC is required to endure an annual 2-day power outage event for facility preventive maintenance and safety inspection of the core electro-mechanical systems. While complete system shut-downs are against the grain of a highly available sub-system, the entire facility must be powered down for a weekend for environmental and safety purposes. The consequence of this ground system outage is far reaching: any science performed on ISS during this outage weekend is lost. Engineering efforts were focused to maximize the ISS investment by engineering a suitable solution capable of continuing HOSC services while supporting safety requirements. The HOSC Power Outage Contingency (HPOC) System is a physically diversified compliment of systems capable of providing identified real-time services for the duration of a planned power outage condition from an alternate control room. HPOC was designed to maintain ISS payload operations for approximately three continuous days during planned HOSC power outages and support a local Payload Operations Team, International Partners, as well as remote users from the alternate control room located in another building.

Quantitative bioanalysis of antibody-conjugated payload in monkey plasma using a hybrid immuno-capture LC-MS/MS approach: Assay development, validation, and a case study.

PubMed

Liu, Ang; Kozhich, Alexander; Passmore, David; Gu, Huidong; Wong, Richard; Zambito, Frank; Rangan, Vangipuram S; Myler, Heather; Aubry, Anne-Françoise; Arnold, Mark E; Wang, Jian

2015-10-01

Antibody drug conjugates (ADCs) are complex molecules composed of two pharmacologically distinct components, the cytotoxic payload and the antibody. The measurement of the payload molecules that are attached to the antibody in vivo is important for the evaluation of the safety and efficacy of ADCs, and can also provide distinct information compared to the antibody-related analytes. However, analyzing the antibody-conjugated payload is challenging and in some cases may not be feasible. The in vivo change in drug antibody ratio (DAR), due to deconjugation, biotransformation or other clearance phenomena, generates unique and additional challenges for ADC analysis in biological samples. Here, we report a novel hybrid approach with immuno-capture of the ADC, payload cleavage by specific enzyme, and LC-MS/MS of the cleaved payload to quantitatively measure the concentration of payload molecules still attached to the antibody via linker in plasma. The ADC reference material used for the calibration curve is not likely to be identical to the ADC measured in study samples due to the change in DAR distribution over the PK time course. The assay clearly demonstrated that there was no bias in the measurement of antibody-conjugated payload for ADC with varying DAR, which thus allowed accurate quantification even when the DAR distribution dynamically changes in vivo. This hybrid assay was fully validated based on a combination of requirements for both chromatographic and ligand binding methods, and was successfully applied to support a GLP safety study in monkeys. Copyright © 2015 Elsevier B.V. All rights reserved.

International Cooperation in the Field of International Space Station Payload Safety: Overcoming Differences and Working for Future

NASA Astrophysics Data System (ADS)

Nakamura, Yasuhiro; Ozawa, Masayuki; Takeyasu, Yoshioka; Griffith, Gerald; Goto, Katsuhito; Mitsui, Masami

2010-09-01

The importance of international cooperation among the International Space Station(ISS) Program participants is ever increasing as the ISS nears assembly complete. In the field of payload safety assurance, NASA and JAXA have enhanced their cooperation level. The authors describe the evolution of cooperation between the two agencies and the challenges encountered and overcame. NASA and JAXA have been working toward development of a NASA Payload Safety Review Panel(PSRP) franchise panel at JAXA for several years. When the JAXA Safety Review Panel(SRP) becomes a fully franchised panel of the NASA PSRP, the JAXA SRP will have the authority review and approve all JAXA ISS payloads operated on USOS and JEM, although NASA and JAXA joint reviews may be conducted as necessary. A NASA PSRP franchised panel at JAXA will streamline the conventional review process. Japanese payload organizations will not have to go through both JAXA and NASA payload safety reviews, while NASA will be relieved of a certain amount of review activities. The persistent efforts have recently born fruit. For the past two years, NASA and JAXA have increased emphasis on efforts to develop a NASA PSRP Franchised Panel at JAXA with concrete results. In 2009, NASA and JAXA signed Charter and Joint Development Plan. At the end of 2009, NASA PSRP transferred some review responsibility to the JAXA SRP under the franchising charter. Although JAXA had long history of reviewing payloads by their own panel prior to NASA PSRP reviews, it took several years for JAXA to receive NASA PSRP approval for delegation of franchised review authority to JAXA. This paper discusses challenges JAXA and NAXA faced. Considerations were required in developing a franchise at JAXA for history and experiences of the JAXA SRP as well as language and cultural differences. The JAXA panel, not only had its own well-established processes and supporting organizational structures which had some differences from its NASA PSRP counterparts, but the JAXA SRP also had a practice of emphasizing pre-coordination instead of addressing issues in formal reviews, reflecting Japanese cultural influences. These points are illustrated in the paper. The authors will also discuss how NASA and JAXA overcame these issues by providing specific examples including review responsibilities of NASA and JAXA panels, panel and supporting positions, and accommodation of language differences. In conclusion, the current status and future plan for NASA PSRP franchise efforts at JAXA are described and significance of having a NASA PSRP franchise panel at JAXA will be reviewed.

Building on the Past- Looking to the Future: Part 2: A Focus on Expanding Horizons

NASA Astrophysics Data System (ADS)

Nash, Sally K.; Rehm, Raymond B.; Wong, Teresa K.; Guidry, Richard W.; Wolf, Scott L.

2010-09-01

The history of space endeavors stretches far from the first liquid-fueled rocket created by the father of modern rocketry, Robert Goddard, in 1926 and will certainly extend far beyond the construction of the International Space Station(ISS) scheduled to be complete with the addition of the Permanent Multipurpose Module on STS-133/ULF5. National Aeronautics and Space Administration(NASA) and the ISS International Partners(IPs) will be the unrelenting venue used to satisfy the curiosities of man as we seek an understanding of space through various experiments(also referred to as payloads) conducted in microgravity. The NASA Payload Safety Review Panel(PSRP) continues to serve as the lead for the review and assessment of payload hardware to assure facility and crew safety. This is the second in a series of papers and presentations that illustrate challenges and lessons learned in the areas of communication, safety requirements, and processes which have been vital to the PSRP.

Building on the Past - Looking to the Future. Part 2: A Focus on Expanding Horizons

NASA Technical Reports Server (NTRS)

Nash, Sally K.; Rehm, Raymond; Wong, Teresa K.; Guidry, Richard; Wolf, Scott L.

2010-01-01

The history of space endeavors stretches far from the first liquid-fueled rocket created by the father of modern rocketry, Robert Goddard, in 1926 and will certainly extend far beyond the construction of the International Space Station (ISS) scheduled to be complete with the addition of the Permanent Multipurpose Module on STS-133/ULF5. National Aeronautics and Space Administration (NASA) and the ISS International Partners (IPs) will be the unrelenting venue used to satisfy the curiosities of man as we seek an understanding of space through various experiments (also referred to as payloads) conducted in microgravity. The NASA Payload Safety Review Panel (PSRP) continues to serve as the lead for the review and assessment of payload hardware to assure facility and crew safety. This is the second in a series of papers and presentations that illustrate challenges and lessons learned in the areas of communication, safety requirements, and processes which have been vital to the PSRP.

14 CFR 435.41 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false General. 435.41 Section 435.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... policy and safety issues related to the proposed reentry of a payload, except a U.S. Government payload...

14 CFR 435.41 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false General. 435.41 Section 435.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... policy and safety issues related to the proposed reentry of a payload, except a U.S. Government payload...

14 CFR 435.41 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false General. 435.41 Section 435.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... policy and safety issues related to the proposed reentry of a payload, except a U.S. Government payload...

14 CFR 435.41 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false General. 435.41 Section 435.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... policy and safety issues related to the proposed reentry of a payload, except a U.S. Government payload...

14 CFR 435.41 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false General. 435.41 Section 435.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... policy and safety issues related to the proposed reentry of a payload, except a U.S. Government payload...

Stocks, Flows, and Distribution of Critical Metals in Embedded Electronics in Passenger Vehicles.

PubMed

Restrepo, Eliette; Løvik, Amund N; Wäger, Patrick; Widmer, Rolf; Lonka, Radek; Müller, Daniel B

2017-02-07

One of the major applications of critical metals (CMs) is in electrical and electronic equipment (EEE), which is increasingly embedded in other products, notably passenger vehicles. However, recycling strategies for future CM quantities in end-of-life vehicles (ELVs) are poorly understood, mainly due to a limited understating of the complexity of automotive embedded EEE. We introduce a harmonization of the network structure of automotive electronics that enables a comprehensive quantification of CMs in all embedded EEE in a vehicle. This network is combined with a material flow analysis along the vehicle lifecycle in Switzerland to quantify the stocks and flows of Ag, Au, Pd, Ru, Dy, La, Nd, and Co in automotive embedded EEE. In vehicles in use, we calculated 5 -2 +3 t precious metals in controllers embedded in all vehicle types and 220 -60 +90 t rare earth elements (REE); found mainly in five electric motors: alternator, starter, radiator-fan and electronic power steering motor embedded in conventional passenger vehicles and drive motor/generator embedded in hybrid and electric vehicles. Dismantling these devices before ELV shredding, as well as postshredder treatment of automobile shredder residue may increase the recovery of CMs from ELVs. Environmental and economic implications of such recycling strategies must be considered.

Management status of end-of-life vehicles and development strategies of used automotive electronic control components recycling industry in China.

PubMed

Wang, Junjun; Chen, Ming

2012-11-01

Recycling companies play a leading role in the system of end-of-life vehicles (ELVs) in China. Automotive manufacturers in China are rarely involved in recycling ELVs, and they seldom provide dismantling information for recycling companies. In addition, no professional shredding plant is available. The used automotive electronic control components recycling industry in China has yet to take shape because of the lack of supporting technology and profitable models. Given the rapid growth of the vehicle population and electronic control units in automotives in China, the used automotive electronic control components recycling industry requires immediate development. This paper analyses the current recycling system of ELVs in China and introduces the automotive product recycling technology roadmap as well as the recycling industry development goals. The strengths, weaknesses, opportunities and challenges of the current used automotive electronic control components recycling industry in China are analysed comprehensively based on the 'strengths, weaknesses, opportunities and threats' (SWOT) method. The results of the analysis indicate that this recycling industry responds well to all the factors and has good opportunities for development. Based on the analysis, new development strategies for the used automotive electronic control components recycling industry in accordance with the actual conditions of China are presented.

Life cycle assessment of hybrid vehicles recycling: Comparison of three business lines of dismantling.

PubMed

Belboom, Sandra; Lewis, Grégory; Bareel, Pierre-François; Léonard, Angélique

2016-04-01

This paper undertakes an environmental evaluation of hybrid vehicles recycling, using industrial data from Comet Traitement SA in Belgium. Three business lines have been modelled and analysed. The first one is relative to the business as usual with a dismantling to recover batteries and engines followed by shredding and post shredding treatments. The second one considers, in addition, the removal of electronic control units (ECU) before shredding followed by same steps than in the first line and the last one is relative to the additional removal of big plastic parts before shredding and business as usual post shredding treatments. Results show non-significant environmental benefits when ECU or large parts of plastics are recovered before shredding. Improvements in terms of environmental benefits are lower than the uncertainty of the results. Indeed, the performing usual process for end-of-life vehicles (ELV) treatment reaches 97% of the ELV which is valorised in terms of metal and energy recoveries. Post shredding treatment units include metals, plastics and energy recovery of residues. Comet business as usual route for ELV valorisation is in accordance with the requirements of the European directive and recommendations for further improvement with dismantling of other parts (ECU or plastics) before shredding are non-relevant in this case. Copyright © 2016 Elsevier Ltd. All rights reserved.

Subfractionation, characterization and in-depth proteomic analysis of glomerular membrane vesicles in human urine

PubMed Central

Hogan, Marie C.; Johnson, Kenneth L.; Zenka, Roman M.; Charlesworth, M. Cristine; Madden, Benjamin J.; Mahoney, Doug W.; Oberg, Ann L.; Huang, Bing Q.; Nesbitt, Lisa L.; Bakeberg, Jason L.; Bergen, H. Robert; Ward, Christopher J.

2014-01-01

Urinary exosome-like vesicles (ELVs) are a heterogenous mixture (diameter 40–200nm) containing vesicles shed from all segments of the nephron including glomerular podocytes. Contamination with Tamm Horsfall protein (THP) oligomers has hampered their isolation and proteomic analysis. Here we improved ELV isolation protocols employing density centrifugation to remove THP and albumin, and isolated a glomerular membranous vesicle (GMV) enriched subfraction from 7 individuals identifying 1830 proteins and in 3 patients with glomerular disease identifying 5657 unique proteins. The GMV fraction was composed of podocin/podocalyxin positive irregularly shaped membranous vesicles and podocin/podocalyxin negative classical exosomes. Ingenuity pathway analysis identified integrin, actin cytoskeleton and RhoGDI signaling in the top three canonical represented signaling pathways and 19 other proteins associated with inherited glomerular diseases. The GMVs are of podocyte origin and the density gradient technique allowed isolation in a reproducible manner. We show many nephrotic syndrome proteins, proteases and complement proteins involved in glomerular disease are in GMVs and some were shed in the disease state (nephrin, TRPC6 and INF2 and PLA2R). We calculated sample sizes required to identify new glomerular disease biomarkers, expand the ELV proteome and provide a reference proteome in a database that may prove useful in the search for biomarkers of glomerular disease. PMID:24196483

Reentry survivability modeling

NASA Astrophysics Data System (ADS)

Fudge, Michael L.; Maher, Robert L.

1997-10-01

Statistical methods for expressing the impact risk posed to space systems in general [and the International Space Station (ISS) in particular] by other resident space objects have been examined. One of the findings of this investigation is that there are legitimate physical modeling reasons for the common statistical expression of the collision risk. A combination of statistical methods and physical modeling is also used to express the impact risk posed by re-entering space systems to objects of interest (e.g., people and property) on Earth. One of the largest uncertainties in the expressing of this risk is the estimation of survivable material which survives reentry to impact Earth's surface. This point was recently demonstrated in dramatic fashion by the impact of an intact expendable launch vehicle (ELV) upper stage near a private residence in the continental United States. Since approximately half of the missions supporting ISS will utilize ELVs, it is appropriate to examine the methods used to estimate the amount and physical characteristics of ELV debris surviving reentry to impact Earth's surface. This paper examines reentry survivability estimation methodology, including the specific methodology used by Caiman Sciences' 'Survive' model. Comparison between empirical results (observations of objects which have been recovered on Earth after surviving reentry) and Survive estimates are presented for selected upper stage or spacecraft components and a Delta launch vehicle second stage.

14 CFR 1214.608 - Safety requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Safety requirements. 1214.608 Section 1214... Space Shuttle Flights § 1214.608 Safety requirements. The contents of OFK's and PPK's must meet the requirements set forth in NASA Handbook 1700.7, “Safety Policy and Requirements for Payloads Using the Space...

14 CFR 1214.608 - Safety requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Safety requirements. 1214.608 Section 1214... Space Shuttle Flights § 1214.608 Safety requirements. The contents of OFK's and PPK's must meet the requirements set forth in NASA Handbook 1700.7, “Safety Policy and Requirements for Payloads Using the Space...

Life cycle assessment of innovative technology for energy production from automotive shredder residue.

PubMed

Rinaldi, Caterina; Masoni, Paolo; Salvati, Fabio; Tolve, Pietro

2015-07-01

Automotive Shredder Residue (ASR) is a problematic waste material remaining after shredding and recovery processes of end-of-life vehicles (ELVs). Its heterogeneous grain size and composition make difficult its recovery or disposal. Although ASR accounts for approximately 20% to 25% of the weight of an ELV, the European Union (EU)'s ELV Directive (2000/53/EC) requires that by 2015 a minimum 95% of the weight of an ELV must be reused or recovered, including a 10% weight energy recovery. The quantity of ASR is relevant: Approximately 2.4 million tons are generated in the EU each year and most of it is sent to landfills. This article describes a life cycle model of the "TEKNE-Fluff" process designed to make beneficial use of ASR that is based on the results of an experimental pilot plant for pyro-gasification, combustion, cogeneration, and emissions treatment of ASR. The goal of the research was the application of life cycle assessment (LCA) methodology to identify the environmental hot spots of the "TEKNE system" and use scenario analysis to check solutions to improve its environmental profile, supporting the design and industrialization process. The LCA was conducted based on data modeled from the experimental campaign. Moreover, different scenarios on shares of electricity and thermal energy produced by the cogeneration system and alternative treatment processes for the waste produced by the technology were compared. Despite the limitation of the research (results based on scaling up experimental data by modeling), impact assessment results are promising and sufficiently robust, as shown by Monte Carlo analysis. The TEKNE technology may become an interesting solution for the problem of ASR management: Besides representing an alternative to landfill disposal, the energy produced could avoid significant impacts on fossil resources depletion (a plant of 40,000 tons/y capacity could produce ∼ 147,000 GJ/yr, covering the annual need of ∼ 13,500 households). © 2015 SETAC.

Lobar analysis of collapsibility indices to assess functional lung volumes in COPD patients.

PubMed

Kitano, Mariko; Iwano, Shingo; Hashimoto, Naozumi; Matsuo, Keiji; Hasegawa, Yoshinori; Naganawa, Shinji

2014-01-01

We investigated correlations between lung volume collapsibility indices and pulmonary function test (PFT) results and assessed lobar differences in chronic obstructive pulmonary disease (COPD) patients, using paired inspiratory and expiratory three dimensional (3D) computed tomography (CT) images. We retrospectively assessed 28 COPD patients who underwent paired inspiratory and expiratory CT and PFT exams on the same day. A computer-aided diagnostic system calculated total lobar volume and emphysematous lobar volume (ELV). Normal lobar volume (NLV) was determined by subtracting ELV from total lobar volume, both for inspiratory phase (NLVI) and for expiratory phase (NLVE). We also determined lobar collapsibility indices: NLV collapsibility ratio (NLVCR) (%)=(1-NLVE/NLVI)×100%. Associations between lobar volumes and PFT results, and collapsibility indices and PFT results were determined by Pearson correlation analysis. NLVCR values were significantly correlated with PFT results. Forced expiratory volume in 1 second, measured as percent of predicted results (FEV1%P) was significantly correlated with NLVCR values for the lower lobes (P<0.01), whereas this correlation was not significant for the upper lobes (P=0.05). FEV1%P results were also moderately correlated with inspiratory, expiratory ELV (ELVI,E) for the lower lobes (P<0.05). In contrast, the ratio of the diffusion capacity for carbon monoxide to alveolar gas volume, measured as percent of predicted (DLCO/VA%P) results were strongly correlated with ELVI for the upper lobes (P<0.001), whereas this correlation with NLVCR values was weaker for upper lobes (P<0.01) and was not significant for the lower lobes (P=0.26). FEV1%P results were correlated with NLV collapsibility indices for lower lobes, whereas DLCO/VA%P results were correlated with NLV collapsibility indices and ELV for upper lobes. Thus, evaluating lobar NLV collapsibility might be useful for estimating pulmonary function in COPD patients.

Optimization of wet shaking table process using response surface methodology applied to the separation of copper and aluminum from the fine fraction of shredder ELVs.

PubMed

Jordão, Helga; Sousa, António Jorge; Carvalho, M Teresa

2016-02-01

With the purpose of reducing the waste generated by end-of-life vehicles (ELVs) by enhancing the recovery and recycling of nonferrous metals, an experimental study was conducted with the finest size fraction of nonferrous stream produced at an ELV shredder plant. The aim of this work was to characterize the nonferrous stream and to evaluate the efficiency of a gravity concentration process in separating light and heavy nonferrous metal particles that could be easily integrated in a ELV shredder plant (in this case study the separation explicitly addressed copper and aluminum separation). The characterization of a sample of the 0-10mm particle size fraction showed a mixture of nonferrous metals with a certain degree of impurity due to the present of contaminants such as plastics. The majority of the particles exhibited a wire shape, preventing an efficient separation of materials without prior fragmentation. The gravity concentration process selected for this study was the wet shaking table and three operating parameters of the equipment were manipulated. A full factorial design in combination with a central composite design was employed to model metals recovery. Two second order polynomial equations were successfully fitted to describe the process and predict the recovery of copper and aluminum in Cu concentrate under the conditions of the present study. The optimum conditions were determined to be 11.1° of inclination, 2.8L/min of feed water flow and 4.9L/min of wash water flow. All three final products of the wet shaking table had a content higher than 90% in relation to one of the metals, wherein a Cu concentrate product was obtained with a Cu content of 96%, and 78% of Cu recovery and 2% of Al recovery. Copyright © 2015 Elsevier Ltd. All rights reserved.

Structural Safety of a Hubble Space Telescope Science Instrument

NASA Technical Reports Server (NTRS)

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

1993-01-01

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

Proceedings of the 14th Aerospace Mechanisms Symposium

NASA Technical Reports Server (NTRS)

1980-01-01

Technological areas covered include aviation propulsion, aerodynamic devices, and crew safety; space vehicle propulsion, guidance and control; spacecraft deployment, positioning, and pointing; spacecraft bearings, gimbals, and lubricants; and large space structures. Devices for payload deployment, payload retention, and crew extravehicular activity on the space shuttle orbiter are also described.

Aeronautics and Space Report of the President

NASA Technical Reports Server (NTRS)

2002-01-01

Fiscal Year (FY) 2002 brought advances on many fronts in support of NASA's new vision, announced by Administrator Sean O Keefe on April 12, "to improve life here, to extend life to there, to find life beyond." NASA successfully carried out four Space Shuttle missions, including three to the International Space Station (ISS) and one servicing mission to the Hubble Space Telescope (HST). By the end of the fiscal year, humans had occupied the ISS continuously for 2 years. NASA also managed five expendable launch vehicle (ELV) missions and participated in eight international cooperative ELV launches. In the area of space science, two of the Great Observatories, the Hubble Space Telescope and the Chandra X-Ray Observatory, continued to make spectacular observations. The Mars Global Surveyor and Mars Odyssey carried out their mapping missions of the red planet in unprecedented detail. Among other achievements, the Near Earth Asteroid Rendezvous (NEAR) Shoemaker spacecraft made the first soft landing on an asteroid, and the Solar and Heliospheric Observatory (SOHO) monitored a variety of solar activity, including the largest sunspot observed in 10 years. The education and public outreach program stemming from NASA's space science missions continues to grow. In the area of Earth science, attention focused on completing the first Earth Observing Satellite series. Four spacecraft were successfully launched. The goal is to understand our home planet as a system, as well as how the global environment responds to change. In aerospace technology, NASA conducted studies to improve aviation safety and environmental friendliness, progressed with its Space Launch Initiative Program, and explored a variety of pioneering technologies, including nanotechnology, for their application to aeronautics and aerospace. NASA remained broadly engaged in the international arena and concluded over 60 international cooperative and reimbursable international agreements during FY 2002.

Safety in earth orbit study. Volume 5: Space shuttle payloads: Safety requirements and guidelines on-orbit phase

NASA Technical Reports Server (NTRS)

1972-01-01

Safety requirements and guidelines are listed for the sortie module, upper stage vehicle, and space station for the earth orbit operations of the space shuttle program. The requirements and guidelines are for vehicle design, safety devices, warning devices, operational procedures, and residual hazards.

14 CFR 417.117 - Reviews.

Code of Federal Regulations, 2011 CFR

2011-01-01

... information: (i) Readiness of launch vehicle and payload. (ii) Readiness of any flight safety system and... of a launch safety review must ensure satisfaction of the following criteria: (i) A launch operator... operator must resolve all safety related action items. (ii) A launch operator must assign and certify...

System cost performance analysis (study 2.3). Volume 1: Executive summary. [unmanned automated payload programs and program planning

NASA Technical Reports Server (NTRS)

Campbell, B. H.

1974-01-01

A study is described which was initiated to identify and quantify the interrelationships between and within the performance, safety, cost, and schedule parameters for unmanned, automated payload programs. The result of the investigation was a systems cost/performance model which was implemented as a digital computer program and could be used to perform initial program planning, cost/performance tradeoffs, and sensitivity analyses for mission model and advanced payload studies. Program objectives and results are described briefly.

Preliminary risk assessment for nuclear waste disposal in space, volume 2

NASA Technical Reports Server (NTRS)

Rice, E. E.; Denning, R. S.; Friedlander, A. L.

1982-01-01

Safety guidelines are presented. Waste form, waste processing and payload fabrication facilities, shipping casks and ground transport vehicles, payload primary container/core, radiation shield, reentry systems, launch site facilities, uprooted space shuttle launch vehicle, Earth packing orbits, orbit transfer systems, and space destination are discussed. Disposed concepts and risks are then discussed.

First Spacelab flight - A status report of the joint ESA/NASA mission

NASA Technical Reports Server (NTRS)

Craft, H. G., Jr.; Sanfourche, J.-P.

1978-01-01

A general overview of the first Spacelab flight is presented and a table is given listing the payload composition. An accommodation study is presented with emphasis on the configuration, mass status, timeline, and experiment interface specifications. Also considered are flight and ground operations, safety factors, and payload specialists training for the first flight.

Respirable Crystalline Silica (RCS) emissions from industrial plants - Results from measurement programmes in Germany

NASA Astrophysics Data System (ADS)

Ehrlich, C.; Noll, G.; Wusterhausen, E.; Kalkoff, W.-D.; Remus, R.; Lehmann, C.

2013-04-01

Numerous research articles dealing with Respirable Crystalline Silica (RCS) in occupational health because epidemiological studies reveal an association between RCS-dust and the development of silicosis as well as an increased probability of developing lung cancer. Research activities about RCS in ambient air are known from US-measurements. However there is a lack of knowledge regarding RCS-emissions in several industrial sectors. Industrial sources of crystalline silica include construction, foundries, glass manufacturing, abrasive blasting or any industrial or commercial use of silica sand, and mining and rock crushing operations. This paper describes a RCS-emission measurement method for stack gases and report results from the German RCS-emission measurement programmes which were used to identify installations and types of industries with the highest concentration levels of RCS in stack gases. A two-stage cascade impactor was used for the measurements which separate particles into the following size fractions: >10 μm, 10-4 μm und <4 μm of aerodynamic diameter. The measurements were carried out according to international sampling standards. The size of crystalline silica particles of most concern are those respirable particles that are smaller than four microns (millionths of a metre), also called particulate matter 4 (PM4). The analytical procedure of determining crystalline silica in emission samples (in the fraction below 4 μm) consists of using x-ray diffraction and infrared spectroscopy methods which are the same methods as used in the field of occupational health. A total of 37 emission measurement campaigns were assessed (112 RCS-samples in nine industrial sectors). The investigated plants are located in different German states such as Bavaria, North Rhine Westphalia, Baden-Wuerttemberg, Rhineland-Palatinate and Saxony-Anhalt. The results of the measurements show that most of the investigated plants can achieve compliance with the newly developed German emission limit value (ELV) of 1 mg m-3. The ELV is expressed as the concentration of RCS in stack emissions. According to the German emission minimising principle and the precautionary principle it is assumed that by complying with the RCS-ELV there is no ambient air health risk for people living these plants. In the case of increased total dust concentration in the stack gas (more than 20 mg m-3) combined with increased percentage of crystalline silica in PM4 dust, a violation of the above mentioned ELV is more likely. This applies mostly to installations in the silica sand processing industry. To comply with the ELV of 1 mg m-3, efficient emission control technology should be implemented and should be well maintained.

A 20k Payload Launch Vehicle Fast Track Development Concept Using an RD-180 Engine and a Centaur Upper Stage

NASA Technical Reports Server (NTRS)

Toelle, Ronald (Compiler)

1995-01-01

A launch vehicle concept to deliver 20,000 lb of payload to a 100-nmi orbit has been defined. A new liquid oxygen/kerosene booster powered by an RD-180 engine was designed while using a slightly modified Centaur upper stage. The design, development, and test program met the imposed 40-mo schedule by elimination of major structural testing by increased factors of safety and concurrent engineering concepts. A growth path to attain 65,000 lb of payload is developed.

A monograph of the National Space Transportation System Office (NSTSO) integration activities conducted at the NASA Lyndon B. Johnson Space Center for the EASE/ACCESS payload flown on STS 61-B

NASA Technical Reports Server (NTRS)

Chassay, Charles

1987-01-01

The integration process of activities conducted at the NASA Lyndon B. Johnson Space Center (JSC) for the Experimental Assembly of Structures in Extravehicular activity (EASE)/Assembly Concept for Construction of Erectable Space Structures (ACCESS) payload is provided as a subset to the standard payload integration process used by the NASA Space Transportation System (STS) to fly payloads on the Space Shuttle. The EASE/ACCESS payload integration activities are chronologically reviewed beginning with the initiation of the flight manifesting and integration process. The development and documentation of the EASE/ACCESS integration requirements are also discussed along with the implementation of the mission integration activities and the engineering assessments supporting the flight integration process. In addition, the STS management support organizations, the payload safety process leading to the STS 61-B flight certification, and the overall EASE/ACCESS integration schedule are presented.

Space-based navigation for RLVs and ELVs

DOT National Transportation Integrated Search

2006-02-08

The Aerospace Corporation was tasked by the Volpe National Transportation System Center to provide technical support to the Federal Aviation Administration, Office of the Associate Administrator for Commercial Space Transportation (FAA/AST), by perfo...

Angular Distribution of light emission in ELVES events

NASA Astrophysics Data System (ADS)

Mussa, Roberto

2017-04-01

The Pierre Auger Observatory, located in Malargüe (Argentina), is the largest facility (3000 kmq ) for the study of Ultra High Energy Cosmic Rays (E>0.3 EeV). The four sites of the Fluorescence Detector (FD) are continuously observing the night sky with moon fraction below 50% (13% duty cycle) with 100 ns time resolution and a space resolution below one degree. Since 2013, the Observatory has implemented a dedicated trigger for the study of ELVES events, produced by lightning activity in Northern Argentina during summer months. A network of ancillary devices (lidars, cloud cameras, weather stations, lightning sensors, E-field mills) complements the FD data to correct for the variation of atmospheric optical properties. This paper will report about the angular distribution of the light emission around the vertical above the lightning source and compare with existing models.

Long-lasting upper D-region ionospheric modifications caused by intense +/- CG lightning discharges

NASA Astrophysics Data System (ADS)

Haldoupis, Christos

2013-04-01

In a recent Geophysical Research Letter we have presented observations from a single maritime storm showing that intense positive cloud-to-ground (+CG) lightning discharges during nighttime, which trigger both an elve and a sprite, are associated with long-lasting conductivity modifications in the upper D-region ionosphere. The ionospheric disturbances can be observed as perturbations in the amplitude and phase of VLF (very low frequency) signals propagating through or near the disturbed region. They are manifested as LOng Recovery early VLF Events (LOREs) which can last up to 20 - 30 minutes. The same ionospheric modifications may also produce abrupt step-like changes in VLF transmissions which offset signal levels for longer times (>30-60 min). Here we discuss these observations supplementing them with new evidence and some statistics. Among other things, the unpublished results show that very intense (currents > 250-300 kA) CG lightning discharges of either positive or negative polarity are always accompanied mainly by step-like LOREs. The evidence suggests that the electromagnetic pulse (EMP) of a very high peak current CG lightning stroke, which is likely able to produce an elve, produces by electron impact long lasting and spatially extended elevations in electron density at VLF ionospheric reflection heights in the upper D region ionosphere. The results identify a mechanism for the LORE VLF signatures and confirm predictions and postulations that elves may be accompanied by significant and long-lasting electron density perturbations in the upper D- lower E- region ionosphere.

STS-107 Payload Specialist Ilan Ramon arrives at KSC for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - STS-107 Payload Specialist Ilan Ramon (the first Israeli astronaut) arrives at KSC to take part in Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Other crew members are Commander Rick Husband, Pilot William 'Willie' McCool, Payload Commander Michael Anderson, Mission Specialists Kalpana Chawla, David Brown and Laurel Clark. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is scheduled for Jan. 16, 2003.

Integration Process for Payloads in the Fluids and Combustion Facility

NASA Technical Reports Server (NTRS)

Free, James M.; Nall, Marsha M.

2001-01-01

The Fluids and Combustion Facility (FCF) is an ISS research facility located in the United States Laboratory (US Lab), Destiny. The FCF is a multi-discipline facility that performs microgravity research primarily in fluids physics science and combustion science. This facility remains on-orbit and provides accommodations to multi-user and Principal investigator (PI) unique hardware. The FCF is designed to accommodate 15 PI's per year. In order to allow for this number of payloads per year, the FCF has developed an end-to-end analytical and physical integration process. The process includes provision of integration tools, products and interface management throughout the life of the payload. The payload is provided with a single point of contact from the facility and works with that interface from PI selection through post flight processing. The process utilizes electronic tools for creation of interface documents/agreements, storage of payload data and rollup for facility submittals to ISS. Additionally, the process provides integration to and testing with flight-like simulators prior to payload delivery to KSC. These simulators allow the payload to test in the flight configuration and perform final facility interface and science verifications. The process also provides for support to the payload from the FCF through the Payload Safety Review Panel (PSRP). Finally, the process includes support in the development of operational products and the operation of the payload on-orbit.

Program test objectives milestone 3. [Integrated Propulsion Technology Demonstrator

NASA Technical Reports Server (NTRS)

Gaynor, T. L.

1994-01-01

The following conclusions have been developed relative to propulsion system technology adequacy for efficient development and operation of recoverable and expendable launch vehicles (RLV and ELV) and the benefits which the integrated propulsion technology demonstrator will provide for enhancing technology: (1) Technology improvements relative to propulsion system design and operation can reduce program cost. Many features or improvement needs to enhance operability, reduce cost, and improve payload are identified. (2) The Integrated Propulsion Technology Demonstrator (IPTD) Program provides a means of resolving the majority of issues associated with improvement needs. (3) The IPTD will evaluate complex integration of vehicle and facility functions in fluid management and propulsion control systems, and provides an environment for validating improved mechanical and electrical components. (4) The IPTD provides a mechanism for investigating operational issues focusing on reducing manpower and time to perform various functions at the launch site. These efforts include model development, collection of data to validate subject models, and ultimate development of complex time line models. (5) The IPTD provides an engine test bed for tri/bi-propellant engine development firings which is representative of the actual vehicle environment. (6) The IPTD provides for only a limited multiengine configuration integration environment for RLV. Multiengine efforts may be simulated for a number of subsystems and a number of subsystems are relatively independent of the multiengine influences.

Ribbon cutting opens new ELV offices

NASA Technical Reports Server (NTRS)

2000-01-01

Center Director Roy Bridges welcomes the audience to a ribbon- cutting ceremony at the E&O Building at KSC. Home for NASA's unmanned missions since 1964, the building has been renovated to house the Expendable Launch Vehicle Program.

Designing an Alternate Mission Operations Control Room

NASA Technical Reports Server (NTRS)

Montgomery, Patty; Reeves, A. Scott

2014-01-01

The Huntsville Operations Support Center (HOSC) is a multi-project facility that is responsible for 24x7 real-time International Space Station (ISS) payload operations management, integration, and control and has the capability to support small satellite projects and will provide real-time support for SLS launches. The HOSC is a serviceoriented/ highly available operations center for ISS payloads-directly supporting science teams across the world responsible for the payloads. The HOSC is required to endure an annual 2-day power outage event for facility preventive maintenance and safety inspection of the core electro-mechanical systems. While complete system shut-downs are against the grain of a highly available sub-system, the entire facility must be powered down for a weekend for environmental and safety purposes. The consequence of this ground system outage is far reaching: any science performed on ISS during this outage weekend is lost. Engineering efforts were focused to maximize the ISS investment by engineering a suitable solution capable of continuing HOSC services while supporting safety requirements. The HOSC Power Outage Contingency (HPOC) System is a physically diversified compliment of systems capable of providing identified real-time services for the duration of a planned power outage condition from an alternate control room. HPOC was designed to maintain ISS payload operations for approximately three continuous days during planned HOSC power outages and support a local Payload Operations Team, International Partners, as well as remote users from the alternate control room located in another building. This paper presents the HPOC architecture and lessons learned during testing and the planned maiden operational commissioning. Additionally, this paper documents the necessity of an HPOC capability given the unplanned HOSC Facility power outage on April 27th, 2011, as a result of the tornado outbreak that damaged the electrical grid to such a degree that significantly inhibited the Tennessee Valley Authority's ability to transmit electricity throughout the North Alabama region.

Test report dot7A type A liquid packaging

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

Ketusky, E. T.; Brandjes, C.; Benoit, T. J.

2017-09-19

This section presents a general description of the DOT Specification 7A Type A liquid content packaging (HVYTAL), the liquid content evaluated as its payload, acceptable payload shipping configurations and features special to its use. This test report documents compliance with the regulatory safety requirements of 49 CFR Parts 173.24, 173.24a, 173.27, 173.410, 173.412, 173.461 – 173.466 and 178.350.

STS-99 crew look over safety equipment during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

At Launch Pad 39A, members of the STS-99 crew and others look over part of the safety equipment. Standing left to right (in uniform) are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Gerhard Thiele and Mamoru Mohri. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

A New Observation Technique Applied to Early/Fast VLF Scattering Events

NASA Astrophysics Data System (ADS)

Kotovsky, D. A.; Moore, R. C.

2012-12-01

Early/fast very low frequency (VLF, 3-30 kHz) events are understood to result from ionospheric conductivity changes associated with lightning. Early/fast amplitude and phase perturbations have been observed coincidentally with various optical observations of transient luminous events (TLEs), including elves, sprites, and sprite halos, each of which can have temporal characteristics consistent with those of early/fast VLF events. It is yet unresolved, however, whether a specific type of TLE is directly related to the ionospheric conductivity changes responsible for the typical early/fast event. In this paper, we present spread spectrum VLF scattering observations of early/fast events. The spread spectrum analysis technique determines the amplitude and phase of a subionospherically propagating VLF signal as a function of time during the early/fast event and as a function of frequency across the 200 Hz bandwidth of the VLF transmission. VLF scattering observations, each identified with causative lightning logged by the National Lightning Detection Network (NLDN), are compared with the predictions of the Long-Wave Propagation Capability (LWPC) code, a three-dimensional earth-ionosphere waveguide propagation and scattering model. Theoretical predictions for VLF scattering from ionization changes associated with elves are compared with those associated with sprite halos, and each are compared with experimental observations. Results indicate that the observed frequency dependence of VLF scattering during early/fast events results from the combination of scattering source properties and Earth-ionosphere waveguide propagation effects. Observations are more consistent with the modeled amplitude perturbations associated with sprite halos than those with elves.

Substance flow analysis and environmental releases of PBDEs in life cycle of automobiles.

PubMed

Choi, Jonghyun; Jang, Yong-Chul; Kim, Jong-Guk

2017-01-01

Polybrominated diphenyl ethers (PBDEs), a class of brominated flame retardants, have been widely used in many applications in industry such as automobiles, textiles, and electronics. This study focused on a quantitative substance flow analysis (SFA) of PBDEs in automobiles in order to identify their flow by life cycle and treatment pathways of PBDEs-containing materials in end-of-life vehicles (ELVs) in Korea. In addition, this study has estimated environmental releases of PBDEs in automobiles by life cycle in Korea. During this study, PBDEs were analyzed for the samples collected from several ELVs treatment facilities using X-ray fluorescence and gas chromatography/mass spectrometry (GC/MS) methods. The system boundary for SFA of PBDEs ranged from manufacturing/trade to disposal stage of automobiles by life cycle. Based on the result of the SFA, it was found that the amount of PBDEs in automobiles were the highest in use stage (7748ton/year), followed by production stage (1743ton/year) in 2014. In disposal stage, automobile shredded residues (ASR) and seat fabrics were the main components with relatively high levels of PBDEs in ELVs. The major treatment methods of such components included incineration (84%), energy recovery (9%), and landfilling (6%). This research indicates that PBDEs were emitted the highest amount from interior components during the use stage of automobiles, followed by recycling processes such as dismantling and shredding. This study suggests that PBDEs in ASR and seat fabrics should be properly managed to prevent the widespread dispersion in the environment. Copyright © 2016 Elsevier B.V. All rights reserved.

The VLF fingerprint of elves: Step-like and long-recovery early VLF perturbations caused by powerful ±CG lightning EM pulses

NASA Astrophysics Data System (ADS)

Haldoupis, Christos; Cohen, Morris; Arnone, Enrico; Cotts, Benjamin; Dietrich, Stefano

2013-08-01

Subionospheric VLF recordings are investigated in relation with intense cloud-to-ground (CG) lightning data. Lightning impacts the lower ionosphere via heating and ionization changes which produce VLF signal perturbations known as early VLF events. Typically, early events recover in about 100 s, but a small subclass does not recover for many minutes, known as long-recovery early events (LORE). In this study, we identify LORE as a distinct category of early VLF events, whose signature may occur either on its own or alongside the short-lived typical early VLF event. Since LORE onsets coincide with powerful lightning strokes of either polarity (±), we infer that they are due to long-lasting ionization changes in the uppermost D region ionosphere caused by electromagnetic pulses emitted by strong ± CG lightning peak currents of typically > 250 kA, which are also known to generate elves. The LORE perturbations are detected when the discharge is located within ~250 km from the great circle path of a VLF transmitter-receiver link. The probability of occurrence increases with stroke intensity and approaches unity for discharges with peak currents ≥ ~300 kA. LOREs are nighttime phenomena that occur preferentially, at least in the present regional data set, during winter when strong ± CG discharges are more frequent and intense. The evidence suggests LORE as a distinct signature representing the VLF fingerprint of elves, a fact which, although was predicted by theory, it escaped identification in the long-going VLF research of lightning effects in the lower ionosphere.

Twenty-Second Annual NASA Supply and Equipment Management Conference

NASA Technical Reports Server (NTRS)

1989-01-01

The status of actions from the 1988 conference is reviewed. Environmental safety issues, definitions, and regulations; contract transition, payload logistics transition, and safety and support equipment; supply products and services, bar code technology, and inventory accuracy; equipment management workshop topics; and contract property workshop topics are outlined.

Space weather biological and systems effects for suborbital flights

DOT National Transportation Integrated Search

2008-10-31

The Aerospace Corporation was tasked to assess the impacts of space weather on both RLVs and ELVs operating at suborbital altitudes from launch sites located in the low (equatorial regions), middle, and high latitudes. The present report presents a b...

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...

Use of COTS Batteries on ISS and Shuttle: Payload Safety and Mission Success

NASA Technical Reports Server (NTRS)

Jeevarajan, Judith A.

2004-01-01

Contents: Current program requirements; Challenges with COTS batteries; manned vehicle COTS methodology in use; List of typical flight COTS batteries; Energy content and toxicity; Hazards, failure modes and controls for different battery chemistries; JSC test details; List of incidents from Consumer Protection Safety Commission; Conclusions ans recommendations.

International Space Station (ISS)

NASA Image and Video Library

2001-02-01

The International Space Station (ISS) Payload Operations Center (POC) at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, is the world's primary science command post for the International Space Station (ISS), the most ambitious space research facility in human history. The Payload Operations team is responsible for managing all science research experiments aboard the Station. The center is also home for coordination of the mission-plarning work of variety of international sources, all science payload deliveries and retrieval, and payload training and safety programs for the Station crew and all ground personnel. Within the POC, critical payload information from the ISS is displayed on a dedicated workstation, reading both S-band (low data rate) and Ku-band (high data rate) signals from a variety of experiments and procedures operated by the ISS crew and their colleagues on Earth. The POC is the focal point for incorporating research and experiment requirements from all international partners into an integrated ISS payload mission plan. This photograph is an overall view of the MSFC Payload Operations Center displaying the flags of the countries participating the ISS. The flags at the left portray The United States, Canada, France, Switzerland, Netherlands, Japan, Brazil, and Sweden. The flags at the right portray The Russian Federation, Italy, Germany, Belgium, Spain, United Kingdom, Denmark, and Norway.

International Space Station (ISS)

NASA Image and Video Library

2000-02-01

The International Space Station (ISS) Payload Operations Center (POC) at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, is the world's primary science command post for the (ISS), the most ambitious space research facility in human history. The Payload Operations team is responsible for managing all science research experiments aboard the Station. The center is also home for coordination of the mission-plarning work of variety of international sources, all science payload deliveries and retrieval, and payload training and safety programs for the Station crew and all ground personnel. Within the POC, critical payload information from the ISS is displayed on a dedicated workstation, reading both S-band (low data rate) and Ku-band (high data rate) signals from a variety of experiments and procedures operated by the ISS crew and their colleagues on Earth. The POC is the focal point for incorporating research and experiment requirements from all international partners into an integrated ISS payload mission plan. This photograph is an overall view of the MSFC Payload Operations Center displaying the flags of the countries participating in the ISS. The flags at the left portray The United States, Canada, France, Switzerland, Netherlands, Japan, Brazil, and Sweden. The flags at the right portray The Russian Federation, Italy, Germany, Belgium, Spain, United Kingdom, Denmark, and Norway.

Bring the "Real World" into the Classroom.

ERIC Educational Resources Information Center

Perkins, Joyce

1991-01-01

Discusses one teacher's methods for familiarizing vocational education students in a business computer applications class with computers. Describes a Christmas project in which the students became Santa's elves to elementary children in the telecommunications community. Describes the project's expansion into an overseas communications service…

The Invisible Elves of the Inclusive School - Paraprofessionals.

ERIC Educational Resources Information Center

Goessling, Deborah Peters

This microethnographic study examined the perspectives of paraprofessionals assisting students with disabilities in inclusive educational settings. Extensive open-ended individual interviews were conducted with 10 educational technicians from 10 different schools in Maine. Demographic data on paraprofessionals in Maine were also analyzed. The…

STS-107 Payload Specialist Ilan Ramon during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, participates in Terminal Countdown Demonstration Test activities, a standard part of Shuttle launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

Proposal for Ground Safety Review Coordination at ISS Launch Sites

NASA Technical Reports Server (NTRS)

Kirkpatrick, Paul D.

2010-01-01

As the transportation of ISS payloads and cargo shifts from KSC to other launch sites, close coordination of ground safety review processes would be of benefit to all parties. The benefit would have the launch sites receiving consistent data that would require less effort to review while still meeting their needs. Until recently, ground safety focus for the ISS program has been almost exclusively for prelaunch processing at KSC/post-landing processing at KSC/DFRC Each launch site, used by the ISS Program, has a ground safety review process. Ground safety viewed as local prerogative. Up till now, ground processing has consisted of low risk/low hazard items; but this will not always be the case. Recent coordination issues associated with the ground safety review of ORU's to be processed at Tanegashima for HTV-2, illustrate that IP ground safety review processes are not well understood by the ISS community at large. Confusion for data providers (US only?). Lack of internal review process for data being submitted to launch sites can lead to inconsistent submittals. NCRs/HRs. Majority of IP ground safety requirements are based upon old KHB 1700.7 (now KNPR 8715.3, Chapter 20). Proposals include: Establish a ground safety working group as part of the MS&MAP. Search for efficiencies in requirements and data submittal processes. Document processes in NSTS 13830/SSP 30599. Each launch site report out its payload ground safety status at the F2F (Monthly's as required). Completions/due dates/NCRs/issues/changes. Establish internal processes for review of ground safety submittals.

International Cooperation of Payload Operations on the International Space Station

NASA Technical Reports Server (NTRS)

Melton, Tina; Onken, Jay

2003-01-01

One of the primary goals of the International Space Station (ISS) is to provide an orbiting laboratory to be used to conduct scientific research and commercial products utilizing the unique environment of space. The ISS Program has united multiple nations into a coalition with the objective of developing and outfitting this orbiting laboratory and sharing in the utilization of the resources available. The primary objectives of the real- time integration of ISS payload operations are to ensure safe operations of payloads, to avoid mutual interference between payloads and onboard systems, to monitor the use of integrated station resources and to increase the total effectiveness of ISS. The ISS organizational architecture has provided for the distribution of operations planning and execution functions to the organizations with expertise to perform each function. Each IPP is responsible for the integration and operations of their payloads within their resource allocations and the safety requirements defined by the joint program. Another area of international cooperation is the sharing in the development and on- orbit utilization of unique payload facilities. An example of this cooperation is the Microgravity Science Glovebox. The hardware was developed by ESA and provided to NASA as part of a barter arrangement.

Identification of Biomarkers for PKD1 Using Urinary Exosomes

PubMed Central

Hogan, Marie C.; Bakeberg, Jason L.; Gainullin, Vladimir G.; Irazabal, Maria V.; Harmon, Amber J.; Lieske, John C.; Charlesworth, M. Cristine; Johnson, Kenneth L.; Madden, Benjamin J.; Zenka, Roman M.; McCormick, Daniel J.; Sundsbak, Jamie L.; Heyer, Christina M.; Torres, Vicente E.; Harris, Peter C.

2015-01-01

Autosomal dominant polycystic kidney disease (ADPKD) is a common cause of ESRD. Affected individuals inherit a defective copy of either PKD1 or PKD2, which encode polycystin-1 (PC1) or polycystin-2 (PC2), respectively. PC1 and PC2 are secreted on urinary exosome-like vesicles (ELVs) (100-nm diameter vesicles), in which PC1 is present in a cleaved form and may be complexed with PC2. Here, label-free quantitative proteomic studies of urine ELVs in an initial discovery cohort (13 individuals with PKD1 mutations and 18 normal controls) revealed that of 2008 ELV proteins, 9 (0.32%) were expressed at significantly different levels in samples from individuals with PKD1 mutations compared to controls (P<0.03). In samples from individuals with PKD1 mutations, levels of PC1 and PC2 were reduced to 54% (P<0.02) and 53% (P<0.001), respectively. Transmembrane protein 2 (TMEM2), a protein with homology to fibrocystin, was 2.1-fold higher in individuals with PKD1 mutations (P<0.03). The PC1/TMEM2 ratio correlated inversely with height-adjusted total kidney volume in the discovery cohort, and the ratio of PC1/TMEM2 or PC2/TMEM2 could be used to distinguish individuals with PKD1 mutations from controls in a confirmation cohort. In summary, results of this study suggest that a test measuring the urine exosomal PC1/TMEM2 or PC2/TMEM2 ratio may have utility in diagnosis and monitoring of polycystic kidney disease. Future studies will focus on increasing sample size and confirming these studies. The data were deposited in the ProteomeXchange (identifier PXD001075). PMID:25475747

Modeling transient luminous events produced by cloud to ground lightning and narrow bipolar pulses: detailed spectra and chemical impact

NASA Astrophysics Data System (ADS)

Perez-Invernon, F. J.; Luque, A.; Gordillo-Vazquez, F. J.

2017-12-01

The electromagnetic field generated by lightning discharges can produce Transient Luminous Events (TLEs) in the lower ionosphere, as previously investigated by many authors. Some recent studies suggest that narrow bipolar pulses (NBP), an impulsive and not well-established type of atmospheric electrical discharge, could also produce TLEs. The characterization and observation of such TLEs could be a source of information about the physics underlying NBP. In this work, we develop two different electrodynamical models to study the impact of lightning-driven electromagnetic fields in the lower ionosphere. The first model calculates the quasi-electrostatic field produced by a single cloud to ground lightning in the terrestrial atmosphere and its influence in the electron transport. This scheme allows us to study halos, a relatively frequent type of TLE. The second model solves the Maxwell equations for the electromagnetic field produced by a lightning discharge coupled with the Langevin's equation for the induced currents in the ionosphere. This model is useful to investigate elves, a fast TLE produced by lightning or by NBP. In addition, both models are coupled with a detailed chemistry of the electronically and vibrationally excited states of molecular nitrogen, allowing us to calculate synthetic spectra of both halos and elves. The models also include a detailed set of kinetic reactions to calculate the temporal evolution of other species. Our results suggest an important enhancement of some molecular species produced by halos, as NOx , N2 O and other metastable species. The quantification of their production could be useful to understand the role of thunderstorms in the climate of our planet. In the case of TLEs produced by NBP, our model confirms the appearance of double elves and allows us to compute their spectral characteristics.

Expert panel answers questions for Super Safety and Health Day at KSC.

NASA Technical Reports Server (NTRS)

1999-01-01

A panel of NASA and contractor senior staff, plus officers from the 45th Space Wing, discuss safety- and health-related concerns in front of an audience of KSC employees, as part of Super Safety and Health Day. Moderating at the podium is Loren Shriver, deputy director for Launch & Payload Processing. Seated left to right are Burt Summerfield, associate director of the Biomedical Office; Colonel William S. Swindling, commander, 45th Medical Group, Patrick Air Force Base, Fla.; Ron Dittemore, manager, Space Shuttle Programs, Johnson Space Center; Roy Bridges, Center Director; Col. Tom Deppe, vice commander, 45th Space Wing, Patrick Air Force Base; Jim Schoefield, program manager, Payload Ground Operations, Boeing; Bill Hickman, program manager, Space Gateway Support; and Ed Adamek, vice president and associate program manager for Ground Operations, United Space Alliance. The panel was one of the presentations during KSC's second annual day-long dedication to safety. Most normal work activities were suspended to allow personnel to attend related activities. The theme, 'Safety and Health Go Hand in Hand,' emphasized KSC's commitment to place the safety and health of the public, astronauts, employees and space-related resources first and foremost. Events also included a keynote address, vendor exhibits, and safety training in work groups. The keynote address and panel session were also broadcast internally over NASA television.

Expert panel answers questions for Super Safety and Health Day at KSC.

NASA Technical Reports Server (NTRS)

1999-01-01

A panel of NASA and contractor senior staff, plus officers from the 45th Space Wing, discuss safety- and health-related concerns in front of an audience of KSC employees as part of Super Safety and Health Day. Moderating at the podium is Loren Shriver, deputy director for Launch & Payload Processing. Seated left to right are Burt Summerfield, associate director of the Biomedical Office; Colonel William S. Swindling, commander, 45th Medical Group, Patrick Air Force Base, Fla.; Ron Dittemore, manager, Space Shuttle Programs, Johnson Space Center; Roy Bridges, Center Director; Col. Tom Deppe, vice commander, 45th Space Wing, Patrick Air Force Base; Jim Schoefield, program manager, Payload Ground Operations, Boeing; Bill Hickman, program manager, Space Gateway Support; and Ed Adamek, vice president and associate program manager for Ground Operations, United Space Alliance. Answering a question at the microphone on the floor is Dave King, director, Shuttle Processing. The panel was one of the presentations during KSC's second annual day-long dedication to safety. Most normal work activities were suspended to allow personnel to attend related activities. The theme, 'Safety and Health Go Hand in Hand,' emphasized KSC's commitment to place the safety and health of the public, astronauts, employees and space- related resources first and foremost. Events also included a keynote address, vendor exhibits, and safety training in work groups. The keynote address and panel session were also broadcast internally over NASA television.

Ammonia Release on ISS

NASA Technical Reports Server (NTRS)

Macatangay, Ariel

2009-01-01

Crew: Approximately 53% metabolic load Product of protein metabolism Limit production of ammonia by external regulation NOT possbile Payloads Potential source Scientific experiments Thorough safety review ensures sufficient levels of containment

Liquid Rocket Engine Testing - Historical Lecture: Simulated Altitude Testing at AEDC

NASA Technical Reports Server (NTRS)

Dougherty, N. S.

2010-01-01

The span of history covered is from 1958 to the present. The outline of this lecture draws from historical examples of liquid propulsion testing done at AEDC primarily for NASA's Marshall Space Flight Center (NASA/MSFC) in the Saturn/Apollo Program and for USAF Space and Missile Systems dual-use customers. NASA has made dual use of Air Force launch vehicles, Test Ranges and Tracking Systems, and liquid rocket altitude test chambers / facilities. Examples are drawn from the Apollo/ Saturn vehicles and the testing of their liquid propulsion systems. Other examples are given to extend to the family of the current ELVs and Evolved ELVs (EELVs), in this case, primarily to their Upper Stages. The outline begins with tests of the XLR 99 Engine for the X-15 aircraft, tests for vehicle / engine induced environments during flight in the atmosphere and in Space, and vehicle staging at high altitude. The discussion is from the author's perspective and background in developmental testing.

Optimal control theory determination of feasible return-to-launch-site aborts for the HL-20 Personnel Launch System vehicle

NASA Technical Reports Server (NTRS)

Dutton, Kevin E.

1994-01-01

The personnel launch system (PLS) being studied by NASA is a system to complement the space shuttle and provide alternative access to space. The PLS consists of a manned spacecraft launched by an expendable launch vehicle (ELV). A candidate for the manned spacecraft is the HL-20 lifting body. In the event of an ELV malfunction during the initial portion of the ascent trajectory, the HL-20 will separate from the rocket and perform an unpowered return to launch site (RTLS) abort. This work details an investigation, using optimal control theory, of the RTLS abort scenario. The objective of the optimization was to maximize final altitude. With final altitude as the cost function, the feasibility of an RTLS abort at different times during the ascent was determined. The method of differential inclusions was used to determine the optimal state trajectories, and the optimal controls were then calculated from the optimal states and state rates.

Multi-criteria decision aid approach for the selection of the best compromise management scheme for ELVs: the case of Cyprus.

PubMed

Mergias, I; Moustakas, K; Papadopoulos, A; Loizidou, M

2007-08-25

Each alternative scheme for treating a vehicle at its end of life has its own consequences from a social, environmental, economic and technical point of view. Furthermore, the criteria used to determine these consequences are often contradictory and not equally important. In the presence of multiple conflicting criteria, an optimal alternative scheme never exists. A multiple-criteria decision aid (MCDA) method to aid the Decision Maker (DM) in selecting the best compromise scheme for the management of End-of-Life Vehicles (ELVs) is presented in this paper. The constitution of a set of alternatives schemes, the selection of a list of relevant criteria to evaluate these alternative schemes and the choice of an appropriate management system are also analyzed in this framework. The proposed procedure relies on the PROMETHEE method which belongs to the well-known family of multiple criteria outranking methods. For this purpose, level, linear and Gaussian functions are used as preference functions.

Preparing safety data packages for experimenters using the Get Away Special (GAS) carrier system

NASA Technical Reports Server (NTRS)

Kosko, Jerome

1992-01-01

The implementation of NSTS 1700.7B and more forceful scruntiny of data packages by the Johnson Space Flight Center (JSC) lead to the development of a classification policy for GAS/CAP payloads. The purpose of this policy is to classify experiments using the carrier system so that they receive an appropriate level of JSC review (i.e., one or multiphase reviews). This policy is based on energy containment to show inherent payload safety. It impacts the approach to performing hazard analyses and the nature of the data package. This paper endeavors to explain the impact of this policy as well as the impact of recent JSC as well as Kennedy Space Flight Center (KSC) 'interpretations' of existing requirements. The GAS canister does adequately contain most experiments when flown in the sealed configuration (however this must be shown, not merely stated). This paper also includes data package preparation guidelines for those experiments that require an opening door which often present unique safety issues.

Loads and low frequency dynamics - An ENVIRONET data base

NASA Technical Reports Server (NTRS)

Garba, John A.

1988-01-01

The loads and low frequency dynamics data base, part of Environet, is described with particular attention given to its development and contents. The objective of the data base is to provide the payload designer with design approaches and design data to meet STS safety requirements. Currently the data base consists of the following sections: abstract, scope, glossary, requirements, interaction with other environments, summary of the loads analysis process, design considerations, guidelines for payload design loads, information data base, and references.

STS-107 Payload Specialist Ilan Ramon suits up for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, gets help with his suitup for Terminal Countdown Demonstration Test activities, which include a simulated launch countdown at the pad. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia. .

Guidelines for mission integration, a summary report

NASA Technical Reports Server (NTRS)

1979-01-01

Guidelines are presented for instrument/experiment developers concerning hardware design, flight verification, and operations and mission implementation requirements. Interface requirements between the STS and instruments/experiments are defined. Interface constraints and design guidelines are presented along with integrated payload requirements for Spacelab Missions 1, 2, and 3. Interim data are suggested for use during hardware development until more detailed information is developed when a complete mission and an integrated payload system are defined. Safety requirements, flight verification requirements, and operations procedures are defined.

Overview of TPS Tasks

NASA Technical Reports Server (NTRS)

Johnson, Sylvia M.

2000-01-01

The objectives of the project summarized in this viewgraph presentation are the following: (1) Develop a lightweight and low cost durable Thermal Protection System (TPS) for easy application to reusable launch vehicle payload launchers; (2) Develop quickly processed composite TPS processing and repair techniques; and (3) Develop higher temperature capability tile TPS. The benefits of this technology include reduced installation and operations cost, enhanced payload capability resulting from TPS weight reduction, and enhanced flight envelope and performance resulting from higher temperature capability TPS which can result in improved safety.

STS-107 Payload Specialist Ilan Ramon suits up for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, sits happily during suitup for Terminal Countdown Demonstration Test activities, which include a simulated launch countdown at the pad. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia. .

Automation of Space Processing Applications Shuttle payloads

NASA Technical Reports Server (NTRS)

Crosmer, W. E.; Neau, O. T.; Poe, J.

1975-01-01

The Space Processing Applications Program is examining the effect of weightlessness on key industrial materials processes, such as crystal growth, fine-grain casting of metals, and production of unique and ultra-pure glasses. Because of safety and in order to obtain optimum performance, some of these processes lend themselves to automation. Automation can increase the number of potential Space Shuttle flight opportunities and increase the overall productivity of the program. Five automated facility design concepts and overall payload combinations incorporating these facilities are presented.

KSC-07pd1811

NASA Image and Video Library

2007-07-08

KENNEDY SPACE CENTER, FLA. -- The payload canister is lifted off its transporter up to the payload changeout room. Inside the canister are the S5 truss, SPACEHAB module and external stowage platform 3, the payload for mission STS-118. The red umbilical lines are still attached. The payloads will be transferred inside the changeout room to wait for Space Shuttle Endeavour to arrive at the pad. The changeout room is the enclosed, environmentally controlled portion of the rotating service structure that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The mission will be Endeavour's first flight in more than four years. The shuttle has undergone extensive modifications, including the addition of safety upgrades already added to shuttles Discovery and Atlantis. Endeavour also features new hardware, such as the Station-to-Shuttle Power Transfer System that will allow the docked shuttle to draw electrical power from the station and extend its visits to the orbiting lab. Space Shuttle Endeavour is targeted for launch on Aug. 7 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

KSC-07pd1813

NASA Image and Video Library

2007-07-08

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39A, the payload canister is lifted up to the payload changeout room. Inside the canister are the S5 truss, SPACEHAB module and external stowage platform 3, the payload for mission STS-118. The red umbilical lines are still attached. The payloads will be transferred inside the changeout room to wait for Space Shuttle Endeavour to arrive at the pad. The changeout room is the enclosed, environmentally controlled portion of the rotating service structure that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The mission will be Endeavour's first flight in more than four years. The shuttle has undergone extensive modifications, including the addition of safety upgrades already added to shuttles Discovery and Atlantis. Endeavour also features new hardware, such as the Station-to-Shuttle Power Transfer System that will allow the docked shuttle to draw electrical power from the station and extend its visits to the orbiting lab. Space Shuttle Endeavour is targeted for launch on Aug. 7 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

Selected results from the ISUAL/FORMOSAT2 mission in a 12-year journey

NASA Astrophysics Data System (ADS)

Chen, A. B. C.; Hsu, R. R.; Su, H. T.; Huang, S. M.; Lee, L. J.; Chou, J. K.; Chang, S. C.; Wu, Y. J.; Peng, K. M.; Liu, T. Y.; Mende, S. B.; Frey, H. U.; Takahashi, Y.; Lee, L. C.

2016-12-01

The ISUAL (Imager of Sprites and Upper Atmospheric Lightning) is a scientific payload onboard the FORMOSAT2 satellite (FS2). It is also the first satellite project with the global survey of transient luminous events (TLEs) as one of the mission objectives. Since the launch of ISUAL/FS2 in 2004, ISUAL has continuously monitored the occurrence of TLEs over the pre-midnight tropical and subtropical regions in the past 12 years until 20 June 2016, due to the failure of two of the four reaction wheels. In her 12-year journey, more than forty-two thousand of TLEs, including the sub-species like elves, sprites, sprite-halos, blue jets and gigantic jets, have been recorded from this space platform. In the meantime, as the supporting facilities to the space-borne ISUAL experiment, ground optical imagery systems have been deployed to observe TLEs occurring near Taiwan and several radio waves detecting ground stations have also been installed to register the lightning- or the TLE-related sferics. From analyzing the observed events and the associated sferics, some important insights on these intriguing thundercloud-top phenomena have been revealed. In this talk, the occurrence, the global distributions, the occurrence rates, and the physical characteristics of TLEs as well as some salient properties of the TLE-producing lightning and the impacts of TLEs on the upper atmosphere revealed by the ISUAL mission will be concisely discussed and summarized.

Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

KSC-00pp0089

NASA Image and Video Library

2000-01-17

At Launch Pad 39A, orbiter Endeavour's open payload bay doors, reflecting the surrounding light, reveal the payload on the Shuttle Radar Topography Mission, STS-99. The mission will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0088

NASA Image and Video Library

2000-01-17

At Launch Pad 39A, orbiter Endeavour's open payload bay doors reveal the payload on the Shuttle Radar Topography Mission, STS-99. The mission will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0090

NASA Image and Video Library

2000-01-17

At Launch Pad 39A, orbiter Endeavour's open payload bay doors, reflecting the surrounding lights, reveal the payload on the Shuttle Radar Topography Mission, STS-99. The mission will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0087

NASA Image and Video Library

2000-01-17

At Launch Pad 39A, orbiter Endeavour's open payload bay doors reveal the payload on the Shuttle Radar Topography Mission, STS-99. The mission will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

Delta Evolution at Røde Elv, Disko Island, Greenland

NASA Astrophysics Data System (ADS)

Kroon, A.; Arngrimson, J.; Bendixen, M.; Sigsgaard, C.

2017-12-01

Ice, snow and freezing temperatures have a large impact on coastal morphodynamics in Arctic polar environments. A recent warming of the Arctic climate induces many changes along the arctic shorelines. Sea-levels are rising due to thermal expansion and due to an increased fresh water flux from the glaciers and land ice masses. At the same time, the ice coverage of the coastal waters reduces and the open water periods in summer extend. There is a strong seasonal variation with open waters and active rivers in summer and ice-covered coastal waters and inactive rivers in winter. Coastal processes by waves and tides are thus limited to the summer and early fall. Besides, there is also a strong daily variation in fluvial discharges due to the daily variations in glacier melt with maximum melt in the afternoon and minimum values at night. At the same time, the actual flux of the river to the coastal bay is influenced by the tidal phase. Low tides will enhance the transport to the delta front, while high tides will create stagnant waters over the delta plain. The delta of the Røde Elv is located in southwestern Disko Island in west Greenland. It has a relatively small (ca. 101 km2) and partly glaciated drainage basin (ca. 20%) and its sediments consist of a mixture of basaltic sands and gravels. The Røde Elv delta is located at the end of a pro-glacial and fluvial valley at about 20 km from the glacier. The shores of the delta are reworked by waves, predominantly from southwestern, southern (largest fetch, over 50 km), and southeastern directions. The environment has a micro- to meso- tidal range with a spring tidal range of 2.7 m. The morphologic changes on the delta over the last decades clearly showed a seaward extension of the delta and a periodic shift in the location of the main delta channel. In this presentation, we focus on quantification of water discharges and suspended sediment fluxes to the Røde Elv delta in western Greenland, and on the morphological evolution of the delta over the last decades. We highlight the variation of fluxes over different seasons under changing river discharges and tidal phases. We use field observations of river discharges and sediment fluxes at the lower part of the river close to the delta apex and estimate the wave activity on the delta front using wind and sea ice data and a numerical model computing wave-driven transport rates.

Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch Vehicles

NASA Technical Reports Server (NTRS)

Mullinix, Daniel; Hall, Kenneth; Smith, Bruce; Corbin, Brian

2012-01-01

A low-cost beamformer phased array antenna has been developed for expendable launch vehicles, rockets, and missiles. It utilizes a conformal array antenna of ring or individual radiators (design varies depending on application) that is designed to be fed by the recently developed hybrid electrical/mechanical (vendor-supplied) phased array beamformer. The combination of these new array antennas and the hybrid beamformer results in a conformal phased array antenna that has significantly higher gain than traditional omni antennas, and costs an order of magnitude or more less than traditional phased array designs. Existing omnidirectional antennas for sounding rockets, missiles, and expendable launch vehicles (ELVs) do not have sufficient gain to support the required communication data rates via the space network. Missiles and smaller ELVs are often stabilized in flight by a fast (i.e. 4 Hz) roll rate. This fast roll rate, combined with vehicle attitude changes, greatly increases the complexity of the high-gain antenna beam-tracking problem. Phased arrays for larger ELVs with roll control are prohibitively expensive. Prior techniques involved a traditional fully electronic phased array solution, combined with highly complex and very fast inertial measurement unit phased array beamformers. The functional operation of this phased array is substantially different from traditional phased arrays in that it uses a hybrid electrical/mechanical beamformer that creates the relative time delays for steering the antenna beam via a small physical movement of variable delay lines. This movement is controlled via an innovative antenna control unit that accesses an internal measurement unit for vehicle attitude information, computes a beam-pointing angle to the target, then points the beam via a stepper motor controller. The stepper motor on the beamformer controls the beamformer variable delay lines that apply the appropriate time delays to the individual array elements to properly steer the beam. The array of phased ring radiators is unique in that it provides improved gain for a small rocket or missile that uses spin stabilization for stability. The antenna pattern created is symmetric about the roll axis (like an omnidirectional wraparound), and is thus capable of providing continuous coverage that is compatible with very fast spinning rockets. For larger ELVs with roll control, a linear array of elements can be used for the 1D scanned beamformer and phased array, or a 2D scanned beamformer can be used with an NxN element array.

KSC-99pp0696

NASA Image and Video Library

1999-06-17

A panel of NASA and contractor senior staff, plus officers from the 45th Space Wing, discuss safetyand health-related concerns in front of an audience of KSC employees, as part of Super Safety and Health Day. Moderating at the podium is Loren Shriver, deputy director for Launch & Payload Processing. Seated left to right are Burt Summerfield, associate director of the Biomedical Office; Colonel William S. Swindling, commander, 45th Medical Group, Patrick Air Force Base, Fla.; Ron Dittemore, manager, Space Shuttle Programs, Johnson Space Center; Roy Bridges, Center Director; Col. Tom Deppe, vice commander, 45th Space Wing, Patrick Air Force Base; Jim Schoefield, program manager, Payload Ground Operations, Boeing; Bill Hickman, program manager, Space Gateway Support; and Ed Adamek, vice president and associate program manager for Ground Operations, United Space Alliance. The panel was one of the presentations during KSC's second annual day-long dedication to safety. Most normal work activities were suspended to allow personnel to attend related activities. The theme, "Safety and Health Go Hand in Hand," emphasized KSC's commitment to place the safety and health of the public, astronauts, employees and space-related resources first and foremost. Events also included a keynote address, vendor exhibits, and safety training in work groups. The keynote address and panel session were also broadcast internally over NASA television

Galileo and Ulysses missions safety analysis and launch readiness status

NASA Technical Reports Server (NTRS)

Cork, M. Joseph; Turi, James A.

1989-01-01

The Galileo spacecraft, which will release probes to explore the Jupiter system, was launched in October, 1989 as the payload on STS-34, and the Ulysses spacecraft, which will fly by Jupiter en route to a polar orbit of the sun, is presently entering system-test activity in preparation for an October, 1990 launch. This paper reviews the Galileo and Ulysses mission objectives and design approaches and presents details of the missions' safety analysis. The processes used to develop the safety analysis are described and the results of safety tests are presented.

Test plan and report for Space Shuttle launch environment testing of Bergen cable technology safety cable

NASA Technical Reports Server (NTRS)

Ralph, John

1992-01-01

Bergen Cable Technology (BCT) has introduced a new product they refer to as 'safety cable'. This product is intended as a replacement for lockwire when installed per Aerospace Standard (AS) 4536 (included in Appendix D of this document). Installation of safety cable is reportedly faster and more uniform than lockwire. NASA/GSFC proposes to use this safety cable in Shuttle Small Payloads Project (SSPP) applications on upcoming Shuttle missions. To assure that BCT safety cable will provide positive locking of fasteners equivalent to lockwire, the SSPP will conduct vibration and pull tests of the safety cable.

Internationalizing Technology Teaching with Blogs and Bananas

ERIC Educational Resources Information Center

Davey, Sandy; Smith, Walter S.; Merrill, Chris

2009-01-01

Educators can connect their students internationally in meaningful activities that address multiple teaching standards that are of concern to educators, parents, and the public worldwide. In this article, the authors describe a project wherein Australian Year 7 students made an "Edible Lunar Vehicle" (ELV) together with U.S. college…

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

Code of Federal Regulations, 2012 CFR

2012-10-01

... Space Station activities and Science or Space Exploration activities unrelated to the International... Exploration activities unrelated to the International Space Station that involve a launch, NASA shall require... or Space Exploration Activities unrelated to the International Space Station, in solicitations and...

Implications of Electron Momentum Relaxation Time Scales for Modeling of Transient Electric Fields in the Lower Ionosphere

NASA Astrophysics Data System (ADS)

Pasko, V. P.

2009-12-01

Thomas et al. [JGR, A12306, 2008] has reported lightning-driven electric (E) field pulses at 75-130 km altitude recorded during rocket experiment in 1995 from Wallops Island, Virginia. The measurements were compared to a 2D electromagnetic model of Cho and Rycroft [JASTP, 60,871,1998]. Thomas et al.[2008] indicated that the observed field magnitudes were an order of magnitude lower than predicted by the model and questioned validity of the electromagnetic pulse mechanism of elves. The goal of the present work, which utilizes Monte Carlo and FDTD electromagnetic modeling, is to emphasize range of validity of the local field approximation (LFA) employed in the Cho and Rycroft's [1998] model and other similar models for the cases when weak (~10 mV/m as reported in [Thomas et al., 2008]) E field pulses are considered. Glukhov et al. [GRL, 23, 2193, 1996] and Sukhorukov et al. [GRL, 23, 2911, 1996] performed Monte Carlo simulations for large E fields ~10V/m at typical altitudes of elves, which fully confirmed validity of models of elves based on LFA [Taranenko et al., GRL, 20, 2675, 1993; Inan et al., GRL, 23, 133, 1996]. We demonstrate that the time of relaxation of the momentum of the electron distributions subjected to the external E field scales approximately as 1/E and exceeds 10s of microseconds for E<1V/m at typical altitudes of elves and sprite halos. The weak, ~10mV/m (<18kHz), E field transients observed in the lower ionosphere [Thomas et al., 2008] can not be accurately described in the framework of the self-consistent electron mobility model based on the LFA [e.g.,Cho and Rycroft, 1998]. At lower ionospheric altitudes LFA in which electron mobility reaches equilibrium value defined by the magnitude of the reduced applied E field is only valid for relatively large fields E>1 V/m when fast (10 kHz) processes are considered. The models of elves relying on LFA [e.g., Taranenko et al., 1993; Inan et al., 1996] generally require E>1 V/m for production of observable optical emissions at lower ionospheric altitudes and therefore remain valid, in agreement with original conclusions reached by Glukhov et al. [1996] and Sukhorukov et al. [1996]. Two additional factors may have contributed to the low field magnitudes reported in [Thomas et al., 2008]: 1) The measurements were conducted on September 2, 1995 around evening hours (9:22 PM local time) at which the lower ionosphere likely exhibited enhancement of electron density in comparison with night time conditions employed in modeling; 2) The NLDN deduced peak currents were employed in modeling with lightning current rise time 60 microseconds while NLDN is generally sensitive to LF radiation, which for a typical -CG is emitted during the initial 1-5 microseconds from a vertical part of the return stroke channel a few tens to a few hundreds of meters above the ground [Krider et al., J. Appl. Meteorol., 15, 301, 1976; Orville, BAMS, 2, 180, 2008]. The low pass filtering with 18 kHz cutoff applied to data reported in [Thomas et al., 2008] may contributed to underestimation of magnitudes of observed lightning induced pulses. Modeling results will be presented which illustrate these effects and allow to reach a good agreement with observations in a subset of the cases reported in [Thomas et al., 2008].

Design, Simulation, Software Development, and Testing of a Compact Aircraft Tracking Payload for the CanX-7 Nanosatellite Mission

NASA Astrophysics Data System (ADS)

Bennett, Ian Graham

Automatic Dependent Surveillance-Broadcast (ADS-B) is quickly becoming the new standard for more efficient air traffic control, but as a satellite/ground-based hybrid system it faces limitations on its usefulness over oceans and remote areas. Tracking of aircraft from space presents many challenges that if overcome will greatly increase the safety and efficiency of commercial air travel in these areas. This thesis presents work performed to develop a flight-ready ADS-B receiver payload for the CanX-7 technology demonstration satellite. Work presented includes a simulation of payload performance and coverage area, the design and testing of a single-feed circularly polarized L-band antenna, the design of software to control the payload and manage its data, and verification of the performance of the hardware prior to integration with the satellite and launch. Also included is a short overview of results from the seven-month aircraft tracking campaign conducted with the spacecraft.

Fuzzy crane control with sensorless payload deflection feedback for vibration reduction

NASA Astrophysics Data System (ADS)

Smoczek, Jaroslaw

2014-05-01

Different types of cranes are widely used for shifting cargoes in building sites, shipping yards, container terminals and many manufacturing segments where the problem of fast and precise transferring a payload suspended on the ropes with oscillations reduction is frequently important to enhance the productivity, efficiency and safety. The paper presents the fuzzy logic-based robust feedback anti-sway control system which can be applicable either with or without a sensor of sway angle of a payload. The discrete-time control approach is based on the fuzzy interpolation of the controllers and crane dynamic model's parameters with respect to the varying rope length and mass of a payload. The iterative procedure combining a pole placement method and interval analysis of closed-loop characteristic polynomial coefficients is proposed to design the robust control scheme. The sensorless anti-sway control application developed with using PAC system with RX3i controller was verified on the laboratory scaled overhead crane.

Centaur operations at the space station

NASA Technical Reports Server (NTRS)

Porter, J.; Thompson, W.; Bennett, F.; Holdridge, J.

1987-01-01

A study was conducted on the feasibility of using a Centaur vehicle as a testbed to demonstrate critical OTV technologies at the Space Station. Two Technology Demonstration Missions (TDMs) were identified: (1) Accommodations, and (2) Operations. The Accommodations TDM contained: (1) berthing, (2) checkout, maintenance and safing, and (3) payload integration missions. The Operations TDM contained: (1) a cryogenic propellant resupply mission, and (2) Centaur deployment activities. A modified Space Station Co-Orbiting Platform (COP) was selected as the optimum refueling and launch node due to safety and operational considerations. After completion of the TDMs, the fueled Centaur would carry out a mission to actually test deployment and help offset TDM costs. From the Station, the Centaur could carry a single payload in excess of 20,000 pounds to geosynchronous orbit or multiple payloads.

STS users study (study 2.2). Volume 2: STS users plan (user data requirements) study

NASA Technical Reports Server (NTRS)

Pritchard, E. I.

1975-01-01

Pre-flight scheduling and pre-flight requirements of the space transportation system are discussed. Payload safety requirements, shuttle flight manifests, and interface specifications are studied in detail.

STS-107 Payload Commander Michael Anderson during TCDT M113 training activities

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- -- STS-107 Payload Commander Michael Anderson takes a break during training on the operation of an M113 armored personnel carrier during Terminal Countdown Demonstration Test activities, a standard part of launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

KSC-03pd0105

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. - STS-107 Payload Commander Michael Anderson is happy to being suiting up for launch on mission STS-107. The mission is devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

Hardware interface unit for control of shuttle RMS vibrations

NASA Technical Reports Server (NTRS)

Lindsay, Thomas S.; Hansen, Joseph M.; Manouchehri, Davoud; Forouhar, Kamran

1994-01-01

Vibration of the Shuttle Remote Manipulator System (RMS) increases the time for task completion and reduces task safety for manipulator-assisted operations. If the dynamics of the manipulator and the payload can be physically isolated, performance should improve. Rockwell has developed a self contained hardware unit which interfaces between a manipulator arm and payload. The End Point Control Unit (EPCU) is built and is being tested at Rockwell and at the Langley/Marshall Coupled, Multibody Spacecraft Control Research Facility in NASA's Marshall Space Flight Center in Huntsville, Alabama.

MSFC Skylab airlock module, volume 2. [systems design and performance, systems support activity, and reliability and safety programs

NASA Technical Reports Server (NTRS)

1974-01-01

System design and performance of the Skylab Airlock Module and Payload Shroud are presented for the communication and caution and warning systems. Crew station and storage, crew trainers, experiments, ground support equipment, and system support activities are also reviewed. Other areas documented include the reliability and safety programs, test philosophy, engineering project management, and mission operations support.

Spaceflight Safety on the North Coast of America

NASA Technical Reports Server (NTRS)

Ciancone, Michael L.; Havenhill, Maria T.; Terlep, Judith A.

1996-01-01

Spaceflight Safety (SFS) engineers at NASA Lewis Research Center (LeRC) are responsible for evaluating the microgravity fluids and combustion experiments, payloads and facilities developed at NASA LeRC which are manifested for spaceflight on the Space Shuttle, the Russian space station Mir, and/or the International Space Station (ISS). An ongoing activity at NASA LeRC is the comprehensive training of its SFS engineers through the creation and use of safety tools and processes. Teams of SFS engineers worked on the development of an Internet website (containing a spaceflight safety knowledge database and electronic templates of safety products) and the establishment of a technical peer review process (known as the Safety Assurance for Lewis Spaceflight Activities (SALSA) review).

Further investigations of lightning-induced transient emissions in the OH airglow layer

NASA Astrophysics Data System (ADS)

Huang, Tai-Yin; Kuo, C. L.; Chiang, C. Y.; Chen, A. B.; Su, H. T.; Hsu, R. R.

2010-10-01

A previous study of lightning-induced transient emissions in and below the OH airglow layer using observations by the Imager of Sprites and Upper Atmospheric Lightning (ISUAL) CCD camera onboard the FORMOSAT-II satellite showed that intensity enhancements occurred more frequently in the OH airglow layer. Here we show the results of new observations made in December 2009 and January 2010 using a narrowband 630 nm filter and spectrophotometer and present further analysis. We estimated the N21P intensity enhancements to be ˜65% and 53% of the total intensity enhancements for the two events we analyzed using ISUAL and the spectrophotometer data in conjunction with a model for emissions of light and VLF perturbations from electromagnetic pulse sources (elves). Our analysis indicates that there is still somewhat considerable intensity enhancement (˜1.25 kR) unaccounted for after the N21P contribution has been removed. Our study suggests that there might be OH emissions in elves and that OH species might also be involved in the lightning-induced process and contribute to the intensity enhancements that we observed.

ADELE sensitivity to high-energy radiation from transient luminous events during the Hurricane and Severe Storm Sentinels campaigns

NASA Astrophysics Data System (ADS)

Bowers, G.; Smith, D. M.; Dwyer, J. R.; Cummer, S. A.; Martinez-Mckinney, F.; Kelley, N. A.; Harris, C. B.; Buzbee, P.

2012-12-01

In the summers of 2013 and 2014, UCSC will fly the Airborne Detector for Energetic Lightning Emissions (ADELE) instrument on board one of the Global Hawk aircraft of the NASA Hurricane and Severe Storm Sentinels (HS3) campaign over storms in the Atlantic. In addition to Terrestrial Gamma-ray Flashes (TGFs), which have been observed at gamma-ray energies by satellites such as RHESSI and FERMI, ADELE will also search for high-energy radiation from Transient Luminous Events (TLEs, i.e. elves, gigantic jets, blue jets, sprites, and sprite halos). High-energy radiation is plausible as a byproduct of stepped leaders in jets, streamers in sprites, and acceleration of electrons in the electromagnetic pulse (EMP) that produces elves. Because ADELE will fly at low altitudes, the intensity of radiation from these events could be orders of magnitude higher at ADELE than at satellites in low earth orbit. We will consider the high energy spectra that might be produced by TLEs and estimate to what extent these phenomena can be observed by ADELE on HS3.

KSC-99pp0697

NASA Image and Video Library

1999-06-17

A panel of NASA and contractor senior staff, plus officers from the 45th Space Wing, discuss safetyand health-related concerns in front of an audience of KSC employees as part of Super Safety and Health Day. Moderating at the podium is Loren Shriver, deputy director for Launch & Payload Processing. Seated left to right are Burt Summerfield, associate director of the Biomedical Office; Colonel William S. Swindling, commander, 45th Medical Group, Patrick Air Force Base, Fla.; Ron Dittemore, manager, Space Shuttle Programs, Johnson Space Center; Roy Bridges, Center Director; Col. Tom Deppe, vice commander, 45th Space Wing, Patrick Air Force Base; Jim Schoefield, program manager, Payload Ground Operations, Boeing; Bill Hickman, program manager, Space Gateway Support; and Ed Adamek, vice president and associate program manager for Ground Operations, United Space Alliance. Answering a question at the microphone on the floor is Dave King, director, Shuttle Processing. The panel was one of the presentations during KSC's second annual day-long dedication to safety. Most normal work activities were suspended to allow personnel to attend related activities. The theme, "Safety and Health Go Hand in Hand," emphasized KSC's commitment to place the safety and health of the public, astronauts, employees and space-related resources first and foremost. Events also included a keynote address, vendor exhibits, and safety training in work groups. The keynote address and panel session were also broadcast internally over NASA television

Cargo systems manual: Heat Pipe Performance (HPP) STS-66

NASA Technical Reports Server (NTRS)

Napp, Robert

1994-01-01

The purpose of the cargo systems manual (CSM) is to provide a payload reference document for payload and shuttle flight operations personnel during shuttle mission planning, training, and flight operations. It includes orbiter-to-payload interface information and payload system information (including operationally pertinent payload safety data) that is directly applicable to the Mission Operations Directorate (MOD) role in the payload mission. The primary objectives of the heat pipe performance (HPP) are to obtain quantitative data on the thermal performance of heat pipes in a microgravity environment. This information will increase understanding of the behavior of heat pipes in space and be useful for application to design improvements in heat pipes and associated systems. The purpose of HPP-2 is to establish a complete one-g and zero-g data base for axial groove heat pipes. This data will be used to update and correlate data generated from a heat pipe design computer program called Grooved Analysis Program (GAP). The HPP-2 objectives are to: determine heat transport capacity and conductance for open/closed grooved heat pipes and different Freon volumes (nominal, under, and overcharged) using a uniform heat load; determine heat transport capacity and conductance for single/multiple evaporators using asymmetric heat loads; obtain precise static, spin, and rewicking data points for undercharged pipes; investigate heat flux limits (asymmetric heat loads); and determine effects of positive body force on thermal performance.

Impact of Estimated Liver Volume and Liver Weight on Gender Disparity in Liver Transplantation

PubMed Central

Mindikoglu, Ayse L.; Emre, Sukru H.; Magder, Laurence S.

2012-01-01

OBJECTIVES While lower Model for End-Stage Liver Disease (MELD) scores due to lower levels of serum creatinine in women might account for some gender disparity in liver transplant (LT) rates, even within MELD scores, women are transplanted at lower rates than men. It is unclear what causes this disparity, but transplant candidate-donor liver size mismatch may be a factor. METHODS We analyzed Organ Procurement and Transplantation Network data for patients with end-stage liver disease on the waiting list. Pooled conditional logistic regression analysis was used to assess the association between gender and LT and determine the degree to which this association was explained by lower MELD scores or liver size. RESULTS A total of 28,866 patients and 424,001 person-months were included in the analysis. Median estimated liver volume (eLV) and liver weight (eLW) were significantly lower in women than in men on the LT waiting list (P<0.0001). Controlling for region and blood type, women were 25% less likely to receive LT in a given month compared to men (P<0.0001). When MELD was included in the model, the odds ratio (OR) for gender increased to 0.84 suggesting that 9 percentage points of the 25% gender disparity was due to MELD score. When eLV was added to the model, there was an additional 3% increase in OR of gender suggesting that transplant candidate-donor liver size mismatch is an underlying factor for lower LT rates in women compared to men (OR=0.87, P<0.0001). CONCLUSIONS Lower LT rates among women on the waiting list can be explained in part by lower MELD scores, eLV and eLW than those of men. However; at least half of the gender disparity still remains unexplained. PMID:23008117

High Speed Intensified Video Observations of TLEs in Support of PhOCAL

NASA Technical Reports Server (NTRS)

Lyons, Walter A.; Nelson, Thomas E.; Cummer, Steven A.; Lang, Timothy; Miller, Steven; Beavis, Nick; Yue, Jia; Samaras, Tim; Warner, Tom A.

2013-01-01

The third observing season of PhOCAL (Physical Origins of Coupling to the upper Atmosphere by Lightning) was conducted over the U.S. High Plains during the late spring and summer of 2013. The goal was to capture using an intensified high-speed camera, a transient luminous event (TLE), especially a sprite, as well as its parent cloud-to-ground (SP+CG) lightning discharge, preferably within the domain of a 3-D lightning mapping array (LMA). The co-capture of sprite and its SP+CG was achieved within useful range of an interferometer operating near Rapid City. Other high-speed sprite video sequences were captured above the West Texas LMA. On several occasions the large mesoscale convective complexes (MCSs) producing the TLE-class lightning were also generating vertically propagating convectively generated gravity waves (CGGWs) at the mesopause which were easily visible using NIR-sensitive color cameras. These were captured concurrent with sprites. These observations were follow-ons to a case on 15 April 2012 in which CGGWs were also imaged by the new Day/Night Band on the Suomi NPP satellite system. The relationship between the CGGW and sprite initiation are being investigated. The past year was notable for a large number of elve+halo+sprite sequences sequences generated by the same parent CG. And on several occasions there appear to be prominent banded modulations of the elves' luminosity imaged at >3000 ips. These stripes appear coincident with the banded CGGW structure, and presumably its density variations. Several elves and a sprite from negative CGs were also noted. New color imaging systems have been tested and found capable of capturing sprites. Two cases of sprites with an aurora as a backdrop were also recorded. High speed imaging was also provided in support of the UPLIGHTS program near Rapid City, SD and the USAFA SPRITES II airborne campaign over the Great Plains.

Developing a Peak Wind Probability Forecast Tool for Kennedy Space Center and Cape Canaveral Air Force Station

NASA Technical Reports Server (NTRS)

Lambert, WInifred; Roeder, William

2007-01-01

This conference presentation describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS) in east-central Florida. The peak winds are an important forecast element for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to develop a short-range peak-wind forecast tool to assist in forecasting LCC violations. The tool will include climatologies of the 5-minute mean and peak winds by month, hour, and direction, and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

Statistical Short-Range Guidance for Peak Wind Forecasts on Kennedy Space Center/Cape Canaveral Air Force Station, Phase III

NASA Technical Reports Server (NTRS)

Crawford, Winifred

2010-01-01

This final report describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS). The peak winds are an important forecast element for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to develop a short-range peak-wind forecast tool to assist in forecasting LCC violations.The tool includes climatologies of the 5-minute mean and peak winds by month, hour, and direction, and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

A Peak Wind Probability Forecast Tool for Kennedy Space Center and Cape Canaveral Air Force Station

NASA Technical Reports Server (NTRS)

Crawford, Winifred; Roeder, William

2008-01-01

This conference abstract describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS) in east-central Florida. The peak winds are an important forecast element for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to develop a short-range peak-wind forecast tool to assist in forecasting LCC violatioas.The tool will include climatologies of the 5-minute mean end peak winds by month, hour, and direction, and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

Peak Wind Forecasts for the Launch-Critical Wind Towers on Kennedy Space Center/Cape Canaveral Air Force Station, Phase IV

NASA Technical Reports Server (NTRS)

Crawford, Winifred

2011-01-01

This final report describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS). The peak winds arc an important forecast clement for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to update the statistics in the current peak-wind forecast tool to assist in forecasting LCC violations. The tool includes onshore and offshore flow climatologies of the 5-minute mean and peak winds and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

A study on leakage radiation dose at ELV-4 electron accelerator bunker

NASA Astrophysics Data System (ADS)

Chulan, Mohd Rizal Md; Yahaya, Redzuwan; Ghazali, Abu BakarMhd

2014-09-01

Shielding is an important aspect in the safety of an accelerator and the most important aspects of a bunker shielding is the door. The bunker's door should be designed properly to minimize the leakage radiation and shall not exceed the permitted limit of 2.5μSv/hr. In determining the leakage radiation dose that passed through the door and gaps between the door and the wall, 2-dimensional manual calculations are often used. This method is hard to perform because visual 2-dimensional is limited and is also very difficult in the real situation. Therefore estimation values are normally performed. In doing so, the construction cost would be higher because of overestimate or underestimate which require costly modification to the bunker. Therefore in this study, two methods are introduced to overcome the problem such as simulation using MCNPX Version 2.6.0 software and manual calculation using 3-dimensional model from Autodesk Inventor 2010 software. The values from the two methods were eventually compared to the real values from direct measurements using Ludlum Model 3 with Model 44-9 probe survey meter.

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.

KSC-00pp0047

NASA Image and Video Library

2000-01-13

At Launch Pad 39A, members of the STS-99 crew and others look over part of the safety equipment. Standing left to right (in uniform) are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Gerhard Thiele and Mamoru Mohri. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

A hazard control system for robot manipulators

NASA Technical Reports Server (NTRS)

Carter, Ruth Chiang; Rad, Adrian

1991-01-01

A robot for space applications will be required to complete a variety of tasks in an uncertain, harsh environment. This fact presents unusual and highly difficult challenges to ensuring the safety of astronauts and keeping the equipment they depend on from becoming damaged. The systematic approach being taken to control hazards that could result from introducing robotics technology in the space environment is described. First, system safety management and engineering principles, techniques, and requirements are discussed as they relate to Shuttle payload design and operation in general. The concepts of hazard, hazard category, and hazard control, as defined by the Shuttle payload safety requirements, is explained. Next, it is shown how these general safety management and engineering principles are being implemented on an actual project. An example is presented of a hazard control system for controlling one of the hazards identified for the Development Test Flight (DTF-1) of NASA's Flight Telerobotic Servicer, a teleoperated space robot. How these schemes can be applied to terrestrial robots is discussed as well. The same software monitoring and control approach will insure the safe operation of a slave manipulator under teleoperated or autonomous control in undersea, nuclear, or manufacturing applications where the manipulator is working in the vicinity of humans or critical hardware.

Containment challenges in HPAPI manufacture for ADC generation.

PubMed

Dunny, Elizabeth; O'Connor, Imelda; Bones, Jonathan

2017-06-01

Antibody-drug conjugates (ADCs) are emerging as an impactful class of therapeutics for the treatment of cancer because of their ability to harness the specificity of an antibody and the cytotoxic potential of the payload to target and destroy cancer cells. However, the potent nature of the cytotoxic payload creates associated manufacturing challenges for active pharmaceutical ingredient (API) manufacturers, because huge investment in containment technology is required to ensure the protection of operators and the environment. Here, we examine the differing attitudes to high-potency categorisation and levels of containment control. We also provide an overview of the most widely used containment strategies for facility design, powder handling, purification, analysis, and cleaning. Finally, we briefly consider the health and safety regulatory challenges associated with the manufacture of cytotoxic payloads for use in antibody-drug conjugates. Copyright © 2017 Elsevier Ltd. All rights reserved.

Lessons Learned From the Development, Operation, and Review of Mechanical Systems on the Space Shuttle, International Space Station, and Payloads

NASA Technical Reports Server (NTRS)

Dinsel, Alison; Jermstad, Wayne; Robertson, Brandan

2006-01-01

The Mechanical Design and Analysis Branch at the Johnson Space Center (JSC) is responsible for the technical oversight of over 30 mechanical systems flying on the Space Shuttle Orbiter and the International Space Station (ISS). The branch also has the responsibility for reviewing all mechanical systems on all Space Shuttle and International Space Station payloads, as part of the payload safety review process, through the Mechanical Systems Working Group (MSWG). These responsibilities give the branch unique insight into a large number of mechanical systems, and problems encountered during their design, testing, and operation. This paper contains narrative descriptions of lessons learned from some of the major problems worked on by the branch during the last two years. The problems are grouped into common categories and lessons learned are stated.

Secondary Payload Opportunities on NASA's Space Launch System (SLS) Enable Science and Deep Space Exploration

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). With this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. This first launch of SLS and the Orion Spacecraft is planned no later than November 2018 and will fly along a trans-lunar trajectory, testing the performance of the SLS and Orion systems for future missions. NASA is making investments to expand the science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1) will include thirteen 6U Cubesat small satellites to be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for the advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

Selection of wires and circuit protective devices for STS Orbiter vehicle payload electrical circuits

NASA Technical Reports Server (NTRS)

Gaston, Darilyn M.

1991-01-01

Electrical designers of Orbiter payloads face the challenge of determining proper circuit protection/wire size parameters to satisfy Orbiter engineering and safety requirements. This document is the result of a program undertaken to review test data from all available aerospace sources and perform additional testing to eliminate extrapolation errors. The resulting compilation of data was used to develop guidelines for the selection of wire sizes and circuit protection ratings. The purpose is to provide guidance to the engineering to ensure a design which meets Orbiter standards and which should be applicable to any aerospace design.

STS-107 Mission Specialist David Brown arrives at KSC for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Mission Specialist David Brown arrives at KSC to take part in Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Other crew members are Commander Rick Husband, Pilot William 'Willie' McCool, Payload Commander Michael Anderson, Mission Specialists Kalpana Chawla and Laurel Clark and Payload Specialist Ilan Ramon (the first Israeli astronaut). STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is scheduled for Jan. 16, 2003.

STS-107 Mission Specialist Laurel Clark arrives at KSC for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Mission Specialist Laurel Clark arrives at KSC to take part in Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Other crew members are Commander Rick Husband, Pilot William 'Willie' McCool, Payload Commander Michael Anderson, Mission Specialists Kalpana Chawla and David Brown, and Payload Specialist Ilan Ramon, the first Israeli astronaut. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is scheduled for Jan. 16, 2003.

STS-107 Mission Specialist Kalpana Chawla arrives at KSC for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - STS-107 Mission Specialist Kalpana Chawla arrives at KSC to take part in Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Other crew members are Commander Rick Husband, Pilot William 'Willie' McCool, Payload Commander Michael Anderson, Mission Specialists David Brown and Laurel Clark and Payload Specialist Ilan Ramon (the first Israeli astronaut). STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is scheduled for Jan. 16, 2003.

STS-107 Payload Specialist Ilan Ramon takes a break during TCDT M113 training

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, takes a break during training on the operation of an M113 armored personnel carrier during Terminal Countdown Demonstration Test activities, a standard part of launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

Automated documentation generator for advanced protein crystal growth

NASA Technical Reports Server (NTRS)

Maddux, Gary A.; Provancha, Anna; Chattam, David

1994-01-01

To achieve an environment less dependent on the flow of paper, automated techniques of data storage and retrieval must be utilized. This software system, 'Automated Payload Experiment Tool,' seeks to provide a knowledge-based, hypertext environment for the development of NASA documentation. Once developed, the final system should be able to guide a Principal Investigator through the documentation process in a more timely and efficient manner, while supplying more accurate information to the NASA payload developer. The current system is designed for the development of the Science Requirements Document (SRD), the Experiment Requirements Document (ERD), the Project Plan, and the Safety Requirements Document.

NASA Launch Services Program Overview

NASA Technical Reports Server (NTRS)

Higginbotham, Scott

2016-01-01

The National Aeronautics and Space Administration (NASA) has need to procure a variety of launch vehicles and services for its unmanned spacecraft. The Launch Services Program (LSP) provides the Agency with a single focus for the acquisition and management of Expendable Launch Vehicle (ELV) launch services. This presentation will provide an overview of the LSP and its organization, approach, and activities.

49 CFR 599.201 - Identification of salvage auctions and disposal facilities.

Code of Federal Regulations, 2014 CFR

2014-10-01

... on the Web site at http://www.cars.gov/disposal; or (3) A facility that disposes of vehicles in...) of this section, be currently listed on the Web site at http://www.cars.gov/disposal, as of the date.... (1) A disposal facility that qualifies as such by active membership in ELVS and that fails to...

49 CFR 599.201 - Identification of salvage auctions and disposal facilities.

Code of Federal Regulations, 2012 CFR

2012-10-01

... on the Web site at http://www.cars.gov/disposal; or (3) A facility that disposes of vehicles in...) of this section, be currently listed on the Web site at http://www.cars.gov/disposal, as of the date.... (1) A disposal facility that qualifies as such by active membership in ELVS and that fails to...

49 CFR 599.201 - Identification of salvage auctions and disposal facilities.

Code of Federal Regulations, 2013 CFR

2013-10-01

... on the Web site at http://www.cars.gov/disposal; or (3) A facility that disposes of vehicles in...) of this section, be currently listed on the Web site at http://www.cars.gov/disposal, as of the date.... (1) A disposal facility that qualifies as such by active membership in ELVS and that fails to...

49 CFR 599.201 - Identification of salvage auctions and disposal facilities.

Code of Federal Regulations, 2011 CFR

2011-10-01

... on the Web site at http://www.cars.gov/disposal; or (3) A facility that disposes of vehicles in...) of this section, be currently listed on the Web site at http://www.cars.gov/disposal, as of the date.... (1) A disposal facility that qualifies as such by active membership in ELVS and that fails to...

The Evaluation of the Performed Activities According to ELVES Method

ERIC Educational Resources Information Center

Erdem, Aliye

2018-01-01

Listening habit has an important share in the individual perceiving his/her environment and the world properly and complying with the social environment he/she lives. Because listening is an important skill which enables the individual to use the communication skills he/she learned both at school and out of school properly and to understand…

Distributed Space System Technology Demonstrations with the Emerald Nanosatellite

NASA Technical Reports Server (NTRS)

Twiggs, Robert

2002-01-01

A viewgraph presentation of Distributed Space System Technologies utilizing the Emerald Nanosatellite is shown. The topics include: 1) Structure Assembly; 2) Emerald Mission; 3) Payload and Mission Operations; 4) System and Subsystem Description; and 5) Safety Integration and Testing.

Research, planning, design and development of selected components, subsystems and systems for the Students for the Exploration and Development of Space Satellite (SEDSAT)

NASA Technical Reports Server (NTRS)

Wingo, Dennis

1997-01-01

The work proposed in this task order was successfully accomplished. This is reflected in the approval by three NASA centers of the SEDSAT satellite to fly as a payload on the shuttle. All documentation necessary for evaluation of the satellite as a Shuttle payload was submitted and approved by the appropriate safety boards. The SEASIS instrument was demonstrated to work and its inclusion as a SEDSAT payload was accomplished in the task period. Finally, the SEDSAT interface to the NASA GSFC PES was approved by MSFC and GSFC with no substantive issues outstanding. As of the end of the contract date all milestones were met. However the NASA MSFC SEDS program was cancelled by the center. Since that time SEDSAT has gone on to be manifested on a Delta vehicle.

Space processing applications payload equipment study. Volume 2E: Commercial equipment utility

NASA Technical Reports Server (NTRS)

Smith, A. G. (Editor)

1974-01-01

Examination of commercial equipment technologies revealed that the functional performance requirements of space processing equipment could generally be met by state-of-the-art design practices. Thus, an apparatus could be evolved from a standard item or derived by custom design using present technologies. About 15 percent of the equipment needed has no analogous commercial base of derivation and requires special development. This equipment is involved primarily with contactless heating and position control. The derivation of payloads using commercial equipment sources provides a broad and potentially cost-effective base upon which to draw. The derivation of payload equipment from commercial technologies poses other issues beyond that of the identifiable functional performance, but preliminary results on testing of selected equipment testing appear quite favorable. During this phase of the SPA study, several aspects of commercial equipment utility were assessed and considered. These included safety, packaging and structural, power conditioning (electrical/electronic), thermal and materials of construction.

KSC00pp1657

NASA Image and Video Library

2000-11-07

The STS-97 crew listens to a trainer explain use of the slidewire basket (right) for emergency egress from the Fixed Service Structure. Second from left is Mission Specialist Joe Tanner; next to him in the cap is Capt. George Hoggard, safety trainer with the KSC Fire Department; Pilot Mike Bloomfield; Mission Specialist Carlos Noriega; Commander Brent Jett; and Mission Specialist Marc Garneau. The training is part of Terminal Countdown Demonstration Test (TCDT) activities, which also include a simulated launch countdown and opportunities to inspect the mission payloads in the orbiter’s payload bay. Mission STS-97is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at 10:05 p.m. EST

KSC-00pp1657

NASA Image and Video Library

2000-11-07

The STS-97 crew listens to a trainer explain use of the slidewire basket (right) for emergency egress from the Fixed Service Structure. Second from left is Mission Specialist Joe Tanner; next to him in the cap is Capt. George Hoggard, safety trainer with the KSC Fire Department; Pilot Mike Bloomfield; Mission Specialist Carlos Noriega; Commander Brent Jett; and Mission Specialist Marc Garneau. The training is part of Terminal Countdown Demonstration Test (TCDT) activities, which also include a simulated launch countdown and opportunities to inspect the mission payloads in the orbiter’s payload bay. Mission STS-97is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at 10:05 p.m. EST

Flight qualified solid argon cooler for the BBXRT instrument. [Broad Band X Ray Telescope for ASTRO-1 payload

NASA Technical Reports Server (NTRS)

Cygnarowicz, Thomas A.; Schein, Michael E.; Lindauer, David A.; Scarlotti, Roger; Pederson, Robert

1990-01-01

A solid argon cooler (SAC) for attached Shuttle payloads has been developed and qualified to meet the need for low cost cooling of flight instruments to the temperature range of 60-120 K. The SACs have been designed and tested with the intent of flying them up to five times. Two coolers, as part of the Broad Band X-ray Telescope (BBXRT) instrument on the ASTRO-1 payload, are awaiting launch on Space Shuttle mission STS-35. This paper describes the design, testing and performance of the SAC and its vacuum maintenance system (VMS), used to maintain the argon as a solid during launch delays of up to 5 days. BBXRT cryogen system design features used to satisfy Shuttle safety requirements are discussed, along with SAC ground servicing equipment (GSE) and procedures used to fill, freeze and subcool the argon.

KSC-03pd0110

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- The STS-107 crew heads for the Astrovan and a ride to Launch Pad 39A for liftoff. From left to right are Payload Commander Michael Anderson, Mission Specialist David Brown, Payload Specialist Ilan Ramon, Mission Specialists Laurel Clark and Kalpana Chawla, Mission Commandaer Rick Husband and Pilot William "Willie" McCool. Ramon is the first astronaut from Israel to fly on a Shuttle. The 16-day mission is devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST. [Photo courtesy of Scott Andrews

14 CFR 1214.1704 - Policy.

Code of Federal Regulations, 2011 CFR

2011-01-01

... onboard the Space Shuttle is not required for operation of payloads or for other essential mission... opportunities for future space flight participants, consistent with safety and mission considerations. When NASA... or more Space Shuttle missions in which their participation is desired. A NASA-designated outside...

14 CFR 1214.1704 - Policy.

Code of Federal Regulations, 2013 CFR

2013-01-01

... onboard the Space Shuttle is not required for operation of payloads or for other essential mission... opportunities for future space flight participants, consistent with safety and mission considerations. When NASA... or more Space Shuttle missions in which their participation is desired. A NASA-designated outside...

14 CFR 1214.1704 - Policy.

Code of Federal Regulations, 2010 CFR

2010-01-01

... onboard the Space Shuttle is not required for operation of payloads or for other essential mission... opportunities for future space flight participants, consistent with safety and mission considerations. When NASA... or more Space Shuttle missions in which their participation is desired. A NASA-designated outside...

14 CFR 1214.1704 - Policy.

Code of Federal Regulations, 2012 CFR

2012-01-01

... onboard the Space Shuttle is not required for operation of payloads or for other essential mission... opportunities for future space flight participants, consistent with safety and mission considerations. When NASA... or more Space Shuttle missions in which their participation is desired. A NASA-designated outside...

14 CFR § 1214.1704 - Policy.

Code of Federal Regulations, 2014 CFR

2014-01-01

... onboard the Space Shuttle is not required for operation of payloads or for other essential mission... opportunities for future space flight participants, consistent with safety and mission considerations. When NASA... or more Space Shuttle missions in which their participation is desired. A NASA-designated outside...

Sharing Skills. Hermione Helps--S-P-E-W: Understanding and Creating Acronyms

ERIC Educational Resources Information Center

Stover, Lynne Farrell

2005-01-01

An acronym, a word formed from the first letters of other words, is often used to name products or organizations. For example, when Hermione Granger, a very clever student at Hogwarts School of Witchcraft and Wizardry, is enraged over the wizarding world's treatment of house-elves, she creates an organization to help put an end to this injustice.…

Acoustic Noise Prediction of the Amine Swingbed ISS ExPRESS Rack Payload

NASA Technical Reports Server (NTRS)

Welsh, David; Smith, Holly; Wang, Shuo

2010-01-01

Acoustics plays a vital role in maintaining the health, safety, and comfort of crew members aboard the International Space Station (ISS). In order to maintain this livable and workable environment, acoustic requirements have been established to ensure that ISS hardware and payload developers account for the acoustic emissions of their equipment and develop acoustic mitigations as necessary. These requirements are verified by an acoustic emissions test of the integrated hardware. The Amine Swingbed ExPRESS (Expedite the PRocessing of ExperimentS to Space) rack payload creates a unique challenge to the developers in that the payload hardware is transported to the ISS in phases, making an acoustic emissions test on the integrated flight hardware impossible. In addition, the payload incorporates a high back pressure fan and a diaphragm vacuum pump, which are recognized as significant and complex noise sources. In order to accurately predict the acoustic emissions of the integrated payload, the individual acoustic noise sources and paths are first characterized. These characterizations are conducted though a series of acoustic emissions tests on the individual payload components. Secondly, the individual acoustic noise sources and paths are incorporated into a virtual model of the integrated hardware. The virtual model is constructed with the use of hybrid method utilizing the Finite Element Acoustic (FEA) and Statistical Energy Analysis (SEA) techniques, which predict the overall acoustic emissions. Finally, the acoustic model is validated though an acoustic characterization test performed on an acoustically similar mock-up of the flight unit. The results of the validated acoustic model are then used to assess the acoustic emissions of the flight unit and define further acoustic mitigation efforts.

KSC-05PD-1449

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Pad 39B, the Orbiter Boom Sensor System (OBSS) sensor package is viewed before the orbiter's payload bay doors are closed for launch. Payload bay door closure is a significant milestone in the preparations of Discovery for the first Return to Flight mission, STS-114. This sensor package will provide surface area and depth defect inspection for all the surfaces of the orbiter. It includes an intensified television camera (ITVC) and a laser dynamic range imager, which are mounted on a pan and tilt unit, and a laser camera system (LCS) mounted on a stationary bracket. The package is part of the new safety measures added for all future Space Shuttle missions. During its 12-day mission, Discoverys seven- person crew will test new hardware and techniques to improve Shuttle safety, as well as deliver supplies to the International Space Station. Discoverys payloads include the Multi-Purpose Logistics Module Raffaello, the Lightweight Multi-Purpose Experiment Support Structure Carrier (LMC), and the External Stowage Platform-2 (ESP-2). Raffaello will deliver supplies to the International Space Station including food, clothing and research equipment. The LMC supports a replacement Control Moment Gyroscope and a tile repair sample box. The ESP-2 is outfitted with replacement parts. Launch of mission STS-114 was set for July 13 at the conclusion of the Flight Readiness Review yesterday.

Aerospace Safety Advisory Panel report to the NASA acting administrator

NASA Technical Reports Server (NTRS)

1986-01-01

The level of activity of the Aerospace Safety Advisory Panel was increased smewhat during 1985 in concert with the increased mission rate of the National Space Transportation System, the evolutionary changes in management and operation of that program, and the preparation of the Vandenberg Launch Site; the implementation of the Program Definition Phase of the Space Station Program; and the actual flight testing of the X-29 research aircraft. Impending payload STS missions and NASA's overall aircraft operations are reviewed. The safety aspects of the LEASAT salvage mission were assessed. The findings and recommendation of the committee are summerized.

Radiation Belt Storm Probes (RBSP) Payload Safety Introduction Briefing

NASA Technical Reports Server (NTRS)

Loftin, Chuck; Lampert, Dianna; Herrburger, Eric; Smith, Clay; Hill, Stuart; VonMehlem, Judi

2008-01-01

Mission of the Geospace Radiation Belt Storm Probes (RBSP) is: Gain s cientific understanding (to the point of predictability) of how populations of relativistic electrons and ions in space form or change in response to changes in solar activity and the solar wind.

Payload Instrument Design Rules for Safe and Efficient Flight Operations

NASA Astrophysics Data System (ADS)

Montagnon, E.; Ferri, P.

2004-04-01

Payload operations are often being neglected in favour of optimisation of scientific performance of the instrument design. This has major drawbacks in terms of cost, safety, efficiency of operations and finally science return. By taking operational aspects into account in the early phases of the instrument design, with a minimum more cultural than financial or technological additional effort, many problems can be avoided or minimized, with significant benefits to be gained in the mission execution phases. This paper presents possible improvements based on the use of the telemetry and telecommand packet standard, proper sharing of autonomy functions between instrument and platform, and enhanced interface documents.

Study of space shuttle EVA/IVA support requirements. Volume 2: EVA/IVA tasks, guidelines, and constraints definition

NASA Technical Reports Server (NTRS)

Webbon, B. W.; Copeland, R. J.; Wood, P. W., Jr.; Cox, R. L.

1973-01-01

The guidelines for EVA and IVA tasks to be performed on the space shuttle are defined. In deriving tasks, guidelines, and constraints, payloads were first identified from the mission model. Payload requirements, together with man and manipulator capabilities, vehicle characteristics and operation, and safety considerations led to a definition of candidate tasks. Guidelines and constraints were also established from these considerations. Scenarios were established, and screening criteria, such as commonality of EVA and IVA activities, were applied to derive representative planned and unplanned tasks. The whole spectrum of credible contingency situations with a potential requirement for EVA/IVA was analyzed.

Space Tug avionics definition study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1975-01-01

A top down approach was used to identify, compile, and develop avionics functional requirements for all flight and ground operational phases. Such requirements as safety mission critical functions and criteria, minimum redundancy levels, software memory sizing, power for tug and payload, data transfer between payload, tug, shuttle, and ground were established. Those functional requirements that related to avionics support of a particular function were compiled together under that support function heading. This unique approach provided both organizational efficiency and traceability back to the applicable operational phase and event. Each functional requirement was then allocated to the appropriate subsystems and its particular characteristics were quantified.

MS Peterson and MS Musgrave in payload bay (PLB) during EVA

NASA Technical Reports Server (NTRS)

1983-01-01

Extravehicular mobility unit (EMU) suited Mission Specialist (MS) Peterson, designated EV2, translates from forward payload bay (PLB) to aft bulkhead worksite along port side sill longeron using tether and slidewire system while MS Musgrave, designated EV1, floats on a tether in center of PLB. Inertial Upper Stage (IUS) Airborne Support Equipment (ASE) forward frame and aft frame tilt actuator (AFTA) table appear in front and behind Musgrave and vertical tail and Orbital Maneuvering System (OMS) pods appear in background highlighted against the cloudy surface of Earth. EMU mini workstation extravehicular activity (EVA) crewmember safety tether reel floats on Musgrave's waist tether.

Computer support for cooperative tasks in Mission Operations Centers

NASA Technical Reports Server (NTRS)

Fox, Jeffrey; Moore, Mike

1994-01-01

Traditionally, spacecraft management has been performed by fixed teams of operators in Mission Operations Centers. The team cooperatively: (1) ensures that payload(s) on spacecraft perform their work; and (2) maintains the health and safety of the spacecraft through commanding and monitoring the spacecraft's subsystems. In the future, the task demands will increase and overload the operators. This paper describes the traditional spacecraft management environment and describes a new concept in which groupware will be used to create a Virtual Mission Operations Center. Groupware tools will be used to better utilize available resources through increased automation and dynamic sharing of personnel among missions.

Study of the early signal perturbations due to GJ and Elves using the LWPC code

NASA Astrophysics Data System (ADS)

Nait Amor, Samir; Ghalila, Hassen; Bouderba, Yasmina

2015-04-01

Early events are a Very Low Frequencies (VLF) signal perturbations recorded during a lightning activity. The properties of these signal perturbations and their association to the lightning peak current and/or Transient Luminous Events (TLEs) were widely studied. In a recently analysis a new early signal perturbations whose recovery time persists for several minutes were discovered. The underlying cause of these events is still unclear. In a recently published work, these events were attributed to the lightning peak current and the type of associated TLE. In others, and newly published papers, analyzes were done where all kind of early events were considered. Statistical results showed that the occurrence of long recovery events is independent of the lightning current amplitude and/or TLEs type. To understand which is the main cause of these events, we analyzed two types of early signal perturbations: One was a typical event (~200s time duration) in association with a Gigantic Jet and the second was a long recovery event in association with an elve recorded on December 12 2009 during the EuroSprite campaign. In addition to the VLF signal analysis, we used the Long Wave Propagation Capability (LWPC) code to simulate the unperturbed and perturbed signal parameters (amplitude and phase), to determine the signal modes attenuation coefficient and then to infer the electron density increases in the disturbed region. The results showed that the reference height was reduced from its ambient value (87km) to 66.4 km in the case of the GJ and 74.3 km for the elve. These reference heights decreases affected the propagating signal at the disturbed region by increasing the modes attenuation coefficient. Effectively, the number of modes was reduced from 28 at ambient condition to 9 modes (in the case of GJ) and 17 (in the case of elve). This high attenuation of modes leads to the appearance of null signal perturbations positions due to the interferences. Between two null positions the signal perturbation was negative (or decreasing) and sometimes positive (or increasing). It was also observed from the LWPC code results that the perturbation amplitude was maximum when the perturbed and unperturbed signals were in phase. Thus the main reason of these observations is the modal structure of the signal at the disturbed region and the receiver location. The electron density increases reached 104 cm-3 at 85 km independently on TLE kind. By the use of the signal perturbation parameters due to the long recovery event and the LWPC code, a recovery time profile of the electron density at each height below 87 km is obtained. The first order exponential decay fit gives different recovery constants depending on the height. This is in good agreement with the atmospheric model where the loss terms rates vary with altitude.

MSPR-2 installation and checkout

NASA Image and Video Library

2015-09-01

ISS044E079682 (09/01/2015) --- NASA Astronaut Scott Kelly works inside the U.S. Destiny Laboratory. Destiny is the primary research laboratory for U.S. payloads, supporting a wide range of experiments and studies contributing to health, safety and quality of life for people all over the world.

Error and Uncertainty Analysis for Ecological Modeling and Simulation

DTIC Science & Technology

2001-12-01

management (LRAM) accounting for environmental, training, and economic factors. In the ELVS methodology, soil erosion status is used as a quantitative...Monte-Carlo approach. The optimization is realized through economic functions or on decision constraints, such as, unit sample cost, number of samples... nitrate flux to the Gulf of Mexico. Nature (Brief Communication) 414: 166-167. (Uncertainty analysis done with SERDP software) Gertner, G., G

Liquid Rocket Engine Testing Overview

NASA Technical Reports Server (NTRS)

Rahman, Shamim

2005-01-01

Contents include the following: Objectives and motivation for testing. Technology, Research and Development Test and Evaluation (RDT&E), evolutionary. Representative Liquid Rocket Engine (LRE) test compaigns. Apollo, shuttle, Expandable Launch Vehicles (ELV) propulsion. Overview of test facilities for liquid rocket engines. Boost, upper stage (sea-level and altitude). Statistics (historical) of Liquid Rocket Engine Testing. LOX/LH, LOX/RP, other development. Test project enablers: engineering tools, operations, processes, infrastructure.

Lessons Learned in Cyberspace Security

DTIC Science & Technology

2014-06-01

software; something undesirable is packaged together with something desirable. A classic example was Elf Bowling attachment, which ran rampant through...the authors’ former school. It combined a fun program featuring elves as bowling pins, however it was packaged with SubSeven (Sub7) malware that...allowed remote access to the infected machine. IExpress, which is delivered in the Windows OS, is one of the legitimate tools for packaging multiple

Modification of the Near Surface Region Metastable Phases and Ion Induced Reactions

DTIC Science & Technology

1984-02-03

cell Si Dave Lilienfeld - amorphous Si layer thickness Au diffusion in metallic glasses Dave Lilienfeld & - low temperature Cu diffusion in Si Tim...Sullivan Fritz Stafford - defect characterization in implanted & annealed silicon-on-sapphire Peter Zielinski - Composition of CuZr metallic glass...ribbons 5. Prof. Johnson Dave Kuhn - measurement of Pd layer thickness Alexandra Elve - hydrogen profiles in metals Lauren Heitner - hydrogen diffusion in

Tle Triangulation Campaign by Japanese High School Students as a Space Educational Project of the Ssh Consortium Kochi

NASA Astrophysics Data System (ADS)

Yamamoto, Masa-Yuki; Okamoto, Sumito; Miyoshi, Terunori; Takamura, Yuzaburo; Aoshima, Akira; Hinokuchi, Jin

As one of the space educational projects in Japan, a triangulation observation project of TLE (Transient Luminous Events: sprites, elves, blue-jets, etc.) has been carried out since 2006 in collaboration between 29 Super Science High-schools (SSH) and Kochi University of Technol-ogy (KUT). Following with previous success of sprite observations by "Astro High-school" since 2004, the SSH consortium Kochi was established as a national space educational project sup-ported by Japan Science and Technology Agency (JST). High-sensitivity CCD camera (Watec, Neptune-100) with 6 mm F/1.4 C-mount lens (Fujinon) and motion-detective software (UFO-Capture, SonotaCo) were given to each participating team in order to monitor Northern night sky of Japan with almost full-coverage. During each school year (from April to March in Japan) since 2006, thousands of TLE images were taken by many student teams, with considerably large numbers of successful triangulations, i.e., (School year, Numbers of TLE observations, Numbers of triangulations) are (2006, 43, 3), (2007, 441, 95), (2008, 734, 115), and (2009, 337, 78). Note that, school year in Japan begins on April 1 and ends on March 31. The observation campaign began in December 2006, numbers are as of Feb. 28, 2010. Recently, some high schools started wide field observations using multiple cameras, and others started VLF observations using handmade loop antennae and amplifiers. Infomation exchange among the SSH consortium Kochi is frequently communicated with scientific discussion via KUT's mailing lists. Also, interactions with amateur observers in Japan are made through an internet forum of "SonotaCo Network Japan" (http://sonotaco.jp). Not only as an educational project but also as a scientific one, the project is also in success. In February 2008, simultaneous observations of Elves were obtained, in November 2009 a Giant "Graft-shaped" Sprites driven by Jets was clearly imaged with VLF signals. Most recently, ob-servations of Elves and sprite halos with stripes like wave structures on airglow were successfully imaged in January 2010. In this talk, four years activities of the SSH consortium Kochi will be presented by participating high-school students and teachers with their own impressions.

Re-entry survivability and risk

NASA Astrophysics Data System (ADS)

Fudge, Michael L.

1998-11-01

This paper is the culmination of the research effort which was reported on last year while still in-progress. As previously reported, statistical methods for expressing the impact risk posed to space systems in general [and the International Space Station (ISS) in particular] by other resident space objects have been examined. One of the findings of this investigation is that there are legitimate physical modeling reasons for the common statistical expression of the collision risk. A combination of statistical methods and physical modeling is also used to express the impact risk posed by reentering space systems to objects of interest (e.g., people and property) on Earth. One of the largest uncertainties in the expressing of this risk is the estimation of survivable material which survives reentry to impact Earth's surface. This point was demonstrated in dramatic fashion in January 1997 by the impact of an intact expendable launch vehicle (ELV) upper stage near a private residence in the continental United States. Since approximately half of the missions supporting ISS will utilize ELVs, it is appropriate to examine the methods used to estimate the amount and physical characteristics of ELV debris surviving reentry to impact Earth's surface. This report details reentry survivability estimation methodology, including the specific methodology used by ITT Systems' (formerly Kaman Sciences) 'SURVIVE' model. The major change to the model in the last twelve months has been the increase in the fidelity with which upper- atmospheric aerodynamics has been modeled. This has resulted in an adjustment in the factor relating the amount of kinetic energy loss to the amount of heating entering and reentering body, and also validated and removed the necessity for certain empirically-based adjustments made to the theoretical heating expressions. Comparisons between empirical results (observations of objects which have been recovered on Earth after surviving reentry) and SURVIVE estimates are presented for selected generic upper stage or spacecraft components, a Soyuz launch vehicle second stage, and for a Delta II launch vehicle second stage and its significant components. Significant similarity is demonstrated between the type and dispersion pattern of the recovered debris from the January 1997 Delta II 2nd stage event and the simulation of that reentry and breakup.

The Role of ESA TEC-QTE in the ISS Safety Process

NASA Astrophysics Data System (ADS)

Orlandi, M.; Rohr, T.; Stienstra, M. H.; Semprimoschnig, C.

2013-09-01

On the 17th of July 2000, the Materials and Processes Reciprocal Agreement was signed between NASA and ESA to define the process for selection and certification of materials used in the Space Shuttle and the International Space Station. Consecutively, on the 20th of June 2003 this agreement was extended to the Automated Transport Vehicle (ATV). It is therefore the responsibility of ESA TEC-QTE, the Materials Space Evaluation and Radiation Effects section, part of the Product Assurance and Safety Department, to ensure that all materials, parts and processes of each of the ISS payloads not only function as required but also do not pose a risk to the safety of the crew members. In this context, TEC-QTE provides qualified expertise to support the ESA Flight Safety Review and assesses safety aspects related to manned projects (materials properties, fluid system compatibility, fungus resistance). This is supported by the Materials Space Evaluation and Radiation Effects section's Materials and Electrical Components laboratory having at its disposition a range of facilities designed to perform environmental effects testing of which off-gassing tests according to ECSS-Q-ST-70-29C (equivalent to NASA STD 6001 test 7) and outgassing tests according to ECSS-Q-ST-70-02C (equivalent to ASTM-E-595). The ESA facility to perform flammability tests according to ECSS-Q-ST-70-21A (equivalent to NASA STD 6001 test1) was moved to Astrium Bremen.TEC-QTE is in charge of reviewing and approving, via RFA or MUA , all materials that do not meet safety requirements as well as COTS or CAM (black boxes) equipment.The safety process ends with the issue of the Materials Certification of the reviewed payload hardware that shows compliance with the relevant materials and processes requirements and standards.In addition to the safety related activities for the ISS, specialised TEC-QTE personnel provide measurements of the air quality inside the ATV and assess whether the toxicity index is within requirements.

Challenges of assuring crew safety in space shuttle missions with international cargoes.

PubMed

Vongsouthy, C; Stenger-Nguyen, P A; Nguyen, H V; Nguyen, P H; Huang, M C; Alexander, R G

2004-02-01

The top priority in America's manned space flight program is the assurance of crew and vehicle safety. This priority gained greater focus during and after the Space Shuttle return-to-flight mission (STS-26). One of the interesting challenges has been to assure crew safety and adequate protection of the Space Shuttle, as a national resource, from increasingly diverse cargoes and operations. The control of hazards associated with the deployment of complex payloads and cargoes has involved many international participants. These challenges are examined in some detail along with examples of how crew safety has evolved in the manned space program and how the international partners have addressed various scenarios involving control and mitigation of potential hazards to crew and vehicle safety. c2003 Published by Elsevier Ltd.

RICK BURT AND ANDY SCHORR WITH LAUNCH VEHICLE STAGE ADAPTER

NASA Image and Video Library

2016-09-23

RICK BURT, RIGHT, DIRECTOR OF SAFETY AND MISSION ASSURANCE TALKS WITH ANDY SCHORR, ASSISTANT MANAGER OF THE SPACE LAUNCH SYSTEM'S SPACECRAFT PAYLOAD INTEGRATION AND EVOLUTION OFFICE. BEHIND THEM IS THE LAUNCH VEHICLE STAGE ADAPTOR, WHICH WAS DESIGNED AND MANUFACTURED AT MARSHALL AND WILL CONNECT TWO MAJOR SLS UPPER SECTIONS

14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

Code of Federal Regulations, 2012 CFR

2012-01-01

... debris generation will not result from conversion of energy sources into energy that fragments the vehicle or its payload. Energy sources include, but are not limited to, chemical, pneumatic, and kinetic energy; and (4) Vehicle safety operations personnel shall adhere to the following work and rest standards...

14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

Code of Federal Regulations, 2014 CFR

2014-01-01

... debris generation will not result from conversion of energy sources into energy that fragments the vehicle or its payload. Energy sources include, but are not limited to, chemical, pneumatic, and kinetic energy; and (4) Vehicle safety operations personnel shall adhere to the following work and rest standards...

14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... debris generation will not result from conversion of energy sources into energy that fragments the vehicle or its payload. Energy sources include, but are not limited to, chemical, pneumatic, and kinetic energy; and (4) Vehicle safety operations personnel shall adhere to the following work and rest standards...

14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

Code of Federal Regulations, 2010 CFR

2010-01-01

... debris generation will not result from conversion of energy sources into energy that fragments the vehicle or its payload. Energy sources include, but are not limited to, chemical, pneumatic, and kinetic energy; and (4) Vehicle safety operations personnel shall adhere to the following work and rest standards...

14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

Code of Federal Regulations, 2013 CFR

2013-01-01

... debris generation will not result from conversion of energy sources into energy that fragments the vehicle or its payload. Energy sources include, but are not limited to, chemical, pneumatic, and kinetic energy; and (4) Vehicle safety operations personnel shall adhere to the following work and rest standards...

Manned Orbital Transfer Vehicle (MOTV). Volume 4: Supporting analysis

NASA Technical Reports Server (NTRS)

Boyland, R. E.; Sherman, S. W.; Morfin, H. W.

1979-01-01

Generic missions were defined to enable potential users to determine the parameters for suggested user projects. Mission modes were identified for providing operation, interfaces, performance, and cost data for studying payloads. Safety requirements for emergencies during various phases of the mission are considered with emphasis on radiation hazards.

STS-107 Pilot William 'Willie' McCool arrives at KSC for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - STS-107 Pilot William 'Willie' McCool pauses next to the T-38 jet aircraft in which he flew to KSC. He and the crew are at KSC to take part in Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Other crew members are Commander Rick Husband, Payload Commander Michael Anderson, Mission Specialists Kalpana Chawla, David Brown and Laurel Clark, and Payload Specialist Ilan Ramon, the first Israeli astronaut. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is scheduled for Jan. 16, 2003.

KSC-02pd1925

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- The STS-107 crew poses for a group portrait with the Vehicle Assembly Building in the background. They are at KSC to take part in Terminal Countdown Demonstration Test activities, a standard part of launch preparations. From left to right are Mission Specialists Kalpana Chawla and Laurel Clark, Pilot William "Willie" McCool, Commander Rick Husband, Mission Specialist David Brown, Payload Specialist Ilan Ramon (the first Israeli astronaut), and Payload Commander Michael Anderson. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is targeted for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST.

STS-107 crew meet with media in front of grandstand at KSC

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - The STS-107 crew meet with the media in front of the grandstand. From left are Commander Rick Husband, Pilot William 'Willie' McCool, Payload Specialist Ilan Ramon, Mission Specialist David Brown, Payload Commander Michael Anderson, and Mission Specialists Laurel Clark and Kalpana Chawla. The crew just finished Terminal Countdown Demonstration Test activities, including a simulated launch countdown, in preparation for launch planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. .

KSC-00pp0069

NASA Image and Video Library

2000-01-14

STS-99 Pilot Dominic Gorie suits up in the Operations and Checkout Building, as part of a flight crew equipment fit check, prior to his trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

A Custom Robotic System for Inspecting HEPA Filters in the Payload Changeout Room at the NASA Kennedy Space Center

NASA Technical Reports Server (NTRS)

Spencer, James E., Jr.; Looney, Joe

1994-01-01

In this paper, the prime objective is to describe a custom 4-dof (degree-of-freedom) robotic arm capable of autonomously or telerobotically performing systematic HEPA filter inspection and certification in the Shuttle Launch Pad Payload Changeout Rooms (PCR's) on pads A and B at the Kennedy Space Center, Florida. This HEPA filter inspection robot (HFIR) has been designed to be easily deployable and is equipped with the necessary sensory devices, control hardware, software and man-machine interfaces needed to implement HEPA filter inspection reliably and efficiently without damaging the filters or colliding with existing PCR structures or filters. The main purpose of the HFIR is to implement an automated positioning system to move special inspection sensors in pre-defined or manual patterns for the purpose of verifying filter integrity and efficiency. This will ultimately relieve NASA Payload Operations from significant problems associated with time, cost and personnel safety, impacts realized during non-automated PCR HFIR filter certification.

Commercial Capaciflector

NASA Technical Reports Server (NTRS)

Vranish, John M.

1991-01-01

A capacitive proximity/tactile sensor with unique performance capabilities ('capaciflector' or capacitive reflector) is being developed by NASA/Goddard Space Flight Center (GSFC) for use on robots and payloads in space in the interests of safety, efficiency, and ease of operation. Specifically, this sensor will permit robots and their attached payloads to avoid collisions in space with humans and other objects and to dock these payloads in a cluttered environment. The sensor is simple, robust, and inexpensive to manufacture with obvious and recognized commercial possibilities. Accordingly, NASA/GSFC, in conjunction with industry, is embarking on an effort to 'spin' this technology off into the private sector. This effort includes prototypes aimed at commercial applications. The principles of operation of these prototypes are described along with hardware, software, modelling, and test results. The hardware description includes both the physical sensor in terms of a flexible printed circuit board and the electronic circuitry. The software description will include filtering and detection techniques. The modelling will involve finite element electric field analysis and will underline techniques used for design optimization.

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

Occurrence of brominated diphenyl ethers, dibenzo-p-dioxins and dibenzofurans in foam materials in scrapped car seats from 1985 to 2012.

PubMed

Redin, L; Niinipuu, M; Jansson, S

2017-03-01

The purpose of this study was to evaluate the occurrence of polybrominated diphenyl ethers (PBDEs), dibenzo-p-dioxins (PBDDs) and dibenzofurans (PBDFs) in polyurethane foam (PUF) from car seats of end-of-life vehicles (ELVs) and compare the concentrations of PBDEs with the stipulated regulations in the POP Directive. The method comprised screening by X-ray fluorescence (XRF) and GG-MS analysis. Of 59 tested samples from ELVs, 17 samples showed lines above limit of detection (LOD) levels when screening by XRF. Those samples were selected as replicates and for further analysis by GC-MS. The majority of the studied samples showed low or non-detectable concentrations of PBDEs and PBDD/Fs, but two samples showed concentrations of Σ Te-HpBDEs close to the regulated level for Te-HpBDEs in waste (1000mgkg -1 ); one was slightly higher (1390mgkg -1 ) and the other slightly lower (570mgkg -1 ). It was concluded that brominated pollutants such as Te-HpBDEs occur in low levels in automotive applications in scrapped cars produced in years when brominated flame retardants were used. However, two of the 59 samples tested showed levels close to those stipulated by regulations concerning POPs in waste. Copyright © 2016 Elsevier Ltd. All rights reserved.

Elves, Forbush Decreases and Solar Activity Studies at the Pierre Auger Observatory

NASA Astrophysics Data System (ADS)

Colalillo, Roberta

The Pierre Auger Observatory, designed to observe cosmic rays at the highest energies, can also be a valid ground based instrument for the observation of transient luminous events and for studying the modulation of galactic cosmic rays due to solar activity. The Fluorescence Detector can observe elves, transient luminous emissions from altitudes between 80 and 95 km above sea level, with timescales of tens of microseconds, which are triggered by lightning activity. A dedicated trigger and an extended readout scheme were introduced to enhance detection efficiency of these events and to improve the knowledge of some peculiar characteristics. The low energy mode of the Surface Detector, on the other hand, records variations in the flux of low energy secondary particles with extreme detail. With the Scaler mode, it is possible to register the rate of signals for deposited energies between 15-100 MeV; the Histogram mode, using the calibration peak and charge histograms of the individual pulses detected by each water-Cherenkov station, covers different deposited energy ranges up to 1 GeV. The variations in the flux of galactic cosmic rays have been studied on short and intermediate time scales (Forbush decreases), but also a long-term analysis, which shows the sensitivity of the Observatory to the solar cycle variation, is in progress.

Final payload test results for the RemoveDebris active debris removal mission

NASA Astrophysics Data System (ADS)

Forshaw, Jason L.; Aglietti, Guglielmo S.; Salmon, Thierry; Retat, Ingo; Roe, Mark; Burgess, Christopher; Chabot, Thomas; Pisseloup, Aurélien; Phipps, Andy; Bernal, Cesar; Chaumette, François; Pollini, Alexandre; Steyn, Willem H.

2017-09-01

Since the beginning of the space era, a significant amount of debris has progressively been generated in space. Active Debris Removal (ADR) missions have been suggested as a way of limiting and controlling future growth in orbital space debris by actively deploying vehicles to remove debris. The European Commission FP7-sponsored RemoveDebris mission, which started in 2013, draws on the expertise of some of Europe's most prominent space institutions in order to demonstrate key ADR technologies in a cost effective ambitious manner: net capture, harpoon capture, vision-based navigation, dragsail de-orbiting. This paper provides an overview of some of the final payload test results before launch. A comprehensive test campaign is underway on both payloads and platform. The tests aim to demonstrate both functional success of the experiments and that the experiments can survive the space environment. Space environmental tests (EVT) include vibration, thermal, vacuum or thermal-vacuum (TVAC) and in some cases EMC and shock. The test flow differs for each payload and depends on the heritage of the constituent payload parts. The paper will also provide an update to the launch, expected in 2017 from the International Space Station (ISS), and test philosophy that has been influenced from the launch and prerequisite NASA safety review for the mission. The RemoveDebris mission aims to be one of the world's first in-orbit demonstrations of key technologies for active debris removal and is a vital prerequisite to achieving the ultimate goal of a cleaner Earth orbital environment.

Safety First: Houston, We Have Liftoff!

ERIC Educational Resources Information Center

Roy, Ken

2014-01-01

A thrown basketball, a kicked football, an elastically launched catapult payload, and a free-falling solid fuel or pressurized gas-propelled rocket all have one thing in common. They are all projectiles familiar to elementary students. A projectile is an object thrown with an initial velocity and then allowed to move without thrust along its…

Using computer graphics to enhance astronaut and systems safety

NASA Technical Reports Server (NTRS)

Brown, J. W.

1985-01-01

Computer graphics is being employed at the NASA Johnson Space Center as a tool to perform rapid, efficient and economical analyses for man-machine integration, flight operations development and systems engineering. The Operator Station Design System (OSDS), a computer-based facility featuring a highly flexible and versatile interactive software package, PLAID, is described. This unique evaluation tool, with its expanding data base of Space Shuttle elements, various payloads, experiments, crew equipment and man models, supports a multitude of technical evaluations, including spacecraft and workstation layout, definition of astronaut visual access, flight techniques development, cargo integration and crew training. As OSDS is being applied to the Space Shuttle, Orbiter payloads (including the European Space Agency's Spacelab) and future space vehicles and stations, astronaut and systems safety are being enhanced. Typical OSDS examples are presented. By performing physical and operational evaluations during early conceptual phases. supporting systems verification for flight readiness, and applying its capabilities to real-time mission support, the OSDS provides the wherewithal to satisfy a growing need of the current and future space programs for efficient, economical analyses.

Two stage launch vehicle

NASA Technical Reports Server (NTRS)

1987-01-01

The Advanced Space Design project for 1986-87 was the design of a two stage launch vehicle, representing a second generation space transportation system (STS) which will be needed to support the space station. The first stage is an unmanned winged booster which is fully reusable with a fly back capability. It has jet engines so that it can fly back to the landing site. This adds safety as well as the flexibility to choose alternate landing sites. There are two different second stages. One of the second stages is a manned advanced space shuttle called Space Shuttle II. Space Shuttle II has a payload capability of delivering 40,000 pounds to the space station in low Earth orbit (LEO), and returning 40,000 pounds to Earth. Servicing the space station makes the ability to return a heavy payload to Earth as important as being able to launch a heavy payload. The other second stage is an unmanned heavy lift cargo vehicle with ability to deliver 150,000 pounds of payload to LEO. This vehicle will not return to Earth; however, the engines and electronics can be removed and returned to Earth in the Space Shuttle II. The rest of the vehicle can then be used on orbit for storage or raw materials, supplies, and space manufactured items awaiting transport back to Earth.

Sasquatch Footprint Tool

NASA Technical Reports Server (NTRS)

Bledsoe, Kristin

2013-01-01

The Crew Exploration Vehicle Parachute Assembly System (CPAS) is the parachute system for NASA s Orion spacecraft. The test program consists of numerous drop tests, wherein a test article rigged with parachutes is extracted or released from an aircraft. During such tests, range safety is paramount, as is the recoverability of the parachutes and test article. It is crucial to establish an aircraft release point that will ensure that the article and all items released from it will land in safe locations. A new footprint predictor tool, called Sasquatch, was created in MATLAB. This tool takes in a simulated trajectory for the test article, information about all released objects, and atmospheric wind data (simulated or actual) to calculate the trajectories of the released objects. Dispersions are applied to the landing locations of those objects, taking into account the variability of winds, aircraft release point, and object descent rate. Sasquatch establishes a payload release point (e.g., where the payload will be extracted from the carrier aircraft) that will ensure that the payload and all objects released from it will land in a specified cleared area. The landing locations (the final points in the trajectories) are plotted on a map of the test range. Sasquatch was originally designed for CPAS drop tests and includes extensive information about both the CPAS hardware and the primary test range used for CPAS testing. However, it can easily be adapted for more complex CPAS drop tests, other NASA projects, and commercial partners. CPAS has developed the Sasquatch footprint tool to ensure range safety during parachute drop tests. Sasquatch is well correlated to test data and continues to ensure the safety of test personnel as well as the safe recovery of all equipment. The tool will continue to be modified based on new test data, improving predictions and providing added capability to meet the requirements of more complex testing.

Panel Resource Management (PRM) Implementation and Effects within Safety Review Panel Settings and Dynamics

NASA Technical Reports Server (NTRS)

Taylor, Robert W.; Nash, Sally K.

2007-01-01

While technical training and advanced degree's assure proficiency at specific tasks within engineering disciplines, they fail to address the potential for communication breakdown and decision making errors familiar to multicultural environments where language barriers, intimidating personalities and interdisciplinary misconceptions exist. In an effort to minimize these pitfalls to effective panel review, NASA's lead safety engineers to the ISS Safety Review Panel (SRP), and Payload Safety Review Panel (PSRP) initiated training with their engineers, in conjunction with the panel chairs, and began a Panel Resource Management (PRM) program. The intent of this program focuses on the ability to reduce the barriers inhibiting effective participation from all panel attendees by bolstering participants confidence levels through increased communication skills, situational awareness, debriefing, and a better technical understanding of requirements and systems.

KSC-03pp0147

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Commander Michael Anderson gets help with his launch and entry suit from the Closeout Crew in the White Room. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Behind him is Pilot William "Willie" McCool. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

KSC-02pd1927

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- The STS-107 crew poses for a group portrait with their instructor inside an M113 armored personnel carrier. The crew is participating in Terminal Countdown Demonstration Test activities, a standard part of launch preparations. From left to right are Pilot William "Willie" McCool, Commander Rick Husband, Mission Specialist Laurel Clark, Instructor George Hoggard, Mission Specialist Kalpana Chawla, Payload Specialist Ilan Ramon (the first Israeli astronaut), Payload Commander Michael Anderson, and Mission Specialist David Brown. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

Compact RF ion source for industrial electrostatic ion accelerator

NASA Astrophysics Data System (ADS)

Kwon, Hyeok-Jung; Park, Sae-Hoon; Kim, Dae-Il; Cho, Yong-Sub

2016-02-01

Korea Multi-purpose Accelerator Complex is developing a single-ended electrostatic ion accelerator to irradiate gaseous ions, such as hydrogen and nitrogen, on materials for industrial applications. ELV type high voltage power supply has been selected. Because of the limited space, electrical power, and robust operation, a 200 MHz RF ion source has been developed. In this paper, the accelerator system, test stand of the ion source, and its test results are described.

Compact RF ion source for industrial electrostatic ion accelerator.

PubMed

Kwon, Hyeok-Jung; Park, Sae-Hoon; Kim, Dae-Il; Cho, Yong-Sub

2016-02-01

Korea Multi-purpose Accelerator Complex is developing a single-ended electrostatic ion accelerator to irradiate gaseous ions, such as hydrogen and nitrogen, on materials for industrial applications. ELV type high voltage power supply has been selected. Because of the limited space, electrical power, and robust operation, a 200 MHz RF ion source has been developed. In this paper, the accelerator system, test stand of the ion source, and its test results are described.

Whose Music? Music Education and Cultural Issues: Debates about What Music to Study Can Raise Questions Related to the Very Purpose of Music Education

ERIC Educational Resources Information Center

Rideout, Roger

2005-01-01

Any music teacher who has planned a holiday concert knows about the politics underlying the selection of appropriate music. Some students do not sing carols or cite lyrics that refer to fictional characters such as elves, goblins, or Harry Potter. Still others do not sing the national anthem. To these students or their parents, such songs…

STS 107 Shuttle Press Kit: Providing 24/7 Space Science Research

NASA Technical Reports Server (NTRS)

2002-01-01

Space shuttle mission STS-107, the 28th flight of the space shuttle Columbia and the 113th shuttle mission to date, will give more than 70 international scientists access to both the microgravity environment of space and a set of seven human researchers for 16 uninterrupted days. Columbia's 16-day mission is dedicated to a mixed complement of competitively selected and commercially sponsored research in the space, life and physical sciences. An international crew of seven, including the first Israeli astronaut, will work 24 hours a day in two alternating shifts to carry out experiments in the areas of astronaut health and safety; advanced technology development; and Earth and space sciences. When Columbia is launched from Kennedy Space Center's Launch Pad 39A it will carry a SPACEHAB Research Double Module (RDM) in its payload bay. The RDM is a pressurized environment that is accessible to the crew while in orbit via a tunnel from the shuttle's middeck. Together, the RDM and the middeck will accommodate the majority of the mission's payloads/experiments. STS-107 marks the first flight of the RDM, though SPACEHAB Modules and Cargo Carriers have flown on 17 previous space shuttle missions. Astronaut Rick Husband (Colonel, USAF) will command STS-107 and will be joined on Columbia's flight deck by pilot William 'Willie' McCool (Commander, USN). Columbia will be crewed by Mission Specialist 2 (Flight Engineer) Kalpana Chawla (Ph.D.), Mission Specialist 3 (Payload Commander) Michael Anderson (Lieutenant Colonel, USAF), Mission Specialist 1 David Brown (Captain, USN), Mission Specialist 4 Laurel Clark (Commander, USN) and Payload Specialist 1 Ilan Ramon (Colonel, Israeli Air Force), the first Israeli astronaut. STS-107 marks Husband's second flight into space - he served as pilot during STS-96, a 10-day mission that saw the first shuttle docking with the International Space Station. Husband served as Chief of Safety for the Astronaut Office until his selection to command the STS-107 crew. Anderson and Chawla will also be making their second spaceflights. Anderson first flew on STS-89 in January 1998 (the eighth Shuttle-Mir docking mission) while Chawla flew on STS-87 in November 1997 (the fourth U.S. Microgravity Payload flight). McCool, Brown, Clark and Ramon will be making their first flights into space.

29. DETAIL OF OUTLET DUCTS FOR MST AIRCONDITIONING SYSTEM IN ...

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

29. DETAIL OF OUTLET DUCTS FOR MST AIR-CONDITIONING SYSTEM IN NORTHWEST CORNER OF SLC-3W MST STATION 70.5 (LOWEST PAYLOAD SERVICE STATION). NOTE RING ATTACHMENT FOR PERSONNEL SAFETY HARNESS IN LEFT FOREGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

STS-95 crew members Glenn and Mukai learn about emergency egress system

NASA Technical Reports Server (NTRS)

1998-01-01

STS-95 Pilot Steven W. Lindsey, Payload Specialist John H. Glenn Jr., senator from Ohio, and Payload Specialist Chiaki Mukai, representing the National Space Development Agency of Japan (NASDA), listen to the Safety Egress trainer talk about the emergency egress system from the pad. The STS-95 crew are at KSC to participate in a Terminal Countdown Demonstration Test (TCDT) which includes mission familiarization activities, emergency egress training, and a simulated main engine cut-off exercise. Other crew members are Mission Specialist Scott E. Parazynski, Mission Specialist Pedro Duque of Spain, representing the European Space Agency (ESA), Mission Commander Curtis L. Brown, and Mission Specialist Stephen K. Robinson. The STS-95 mission, targeted for liftoff on Oct. 29, includes research payloads such as the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbital Systems Test Platform, the International Extreme Ultraviolet Hitchhiker, as well as the SPACEHAB single module with experiments on space flight and the aging process. Following the TCDT, the crew will be returning to Houston for final flight preparations.

KSC-00pp0040

NASA Image and Video Library

2000-01-13

In the Operations and Checkout Building, STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, gets help from suit technicians during flight crew equipment fit check prior to his trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0049

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- On the Fixed Service Structure at Launch Pad 39A, STS-99 Mission Specialists Janet Lynn Kavandi (Ph.D.) and Gerhard Thiele, who is with the European Space Agency, look over the emergency egress equipment. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0071

NASA Image and Video Library

2000-01-14

STS-99 Mission Specialist Janice Voss (Ph.D.) suits up in the Operations and Checkout Building, as part of a flight crew equipment fit check, prior to her trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0070

NASA Image and Video Library

2000-01-14

STS-99 Mission Specialist Gerhard Thiele, with the European Space Agency, suits up in the Operations and Checkout Building, as part of a flight crew equipment fit check, prior to his trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0038

NASA Image and Video Library

2000-01-13

STS-99 Mission Specialist Gerhard Thiele, with the European Space Agency, gets help from a suit technician in the Operations and Checkout Building, as part of flight crew equipment fit check, prior to his trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0039

NASA Image and Video Library

2000-01-13

In the Operations and Checkout Building, STS-99 Mission Specialist Janet Lynn Kavandi (Ph.D.) is helped by a suit technician during flight crew equipment fit check prior to her trip to Launch Pad 39A. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

CoNNeCT Antenna Positioning System Dynamic Simulator Modal Model Correlation

NASA Technical Reports Server (NTRS)

Jones, Tevor M.; McNelis, Mark E.; Staab, Lucas D.; Akers, James C.; Suarez, Vicente

2012-01-01

The National Aeronautics and Space Administration (NASA) developed an on-orbit, adaptable, Software Defined Radios (SDR)/Space Telecommunications Radio System (STRS)-based testbed facility to conduct a suite of experiments to advance technologies, reduce risk, and enable future mission capabilities on the International Space Station (ISS). The Communications, Navigation, and Networking reConfigurable Testbed (CoNNeCT) Project will provide NASA, industry, other Government agencies, and academic partners the opportunity to develop and field communications, navigation, and networking technologies in both the laboratory and space environment based on reconfigurable, software-defined radio platforms and the STRS Architecture. The CoNNeCT Payload Operations Nomenclature is "SCAN Testbed," and this nomenclature will be used in all ISS integration, safety, verification, and operations documentation. The SCAN Testbed (payload) is a Flight Releasable Attachment Mechanism (FRAM) based payload that will launch aboard the Japanese H-II Transfer Vehicle (HTV) Multipurpose Exposed Pallet (EP-MP) to the International Space Station (ISS), and will be transferred to the Express Logistics Carrier 3 (ELC3) via Extravehicular Robotics (EVR). The SCAN Testbed will operate on-orbit for a minimum of two years.

CoNNeCT Antenna Positioning System Dynamic Simulator Modal Model Correlation

NASA Technical Reports Server (NTRS)

Jones, Trevor M.; McNelis, Mark E.; Staab, Lucas D.; Akers, James C.; Suarez, Vicente J.

2012-01-01

The National Aeronautics and Space Administration (NASA) developed an on-orbit, adaptable, Software Defined Radios (SDR)/Space Telecommunications Radio System (STRS)-based testbed facility to conduct a suite of experiments to advance technologies, reduce risk, and enable future mission capabilities on the International Space Station (ISS). The Communications, Navigation, and Networking reConfigurable Testbed (CoNNeCT) Project will provide NASA, industry, other Government agencies, and academic partners the opportunity to develop and field communications, navigation, and networking technologies in both the laboratory and space environment based on reconfigurable, software-defined radio platforms and the STRS Architecture. The CoNNeCT Payload Operations Nomenclature is SCAN Testbed, and this nomenclature will be used in all ISS integration, safety, verification, and operations documentation. The SCAN Testbed (payload) is a Flight Releasable Attachment Mechanism (FRAM) based payload that will launch aboard the Japanese H-II Transfer Vehicle (HTV) Multipurpose Exposed Pallet (EP-MP) to the International Space Station (ISS), and will be transferred to the Express Logistics Carrier 3 (ELC3) via Extravehicular Robotics (EVR). The SCAN Testbed will operate on-orbit for a minimum of two years.

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.

PRE_X Programme: Aerothermodynamic Objectives and Aeroshape Definition for in Flight Experiments

NASA Astrophysics Data System (ADS)

Lambert, O.; Tribot, J.-P.; Saint-Cloud, F.

2002-01-01

As the expendable launch vehicles (ELV) are limited in their trend to lower costs, the reusability (Reusable Launch Vehicle, RLV) could be the way to make drastic step. By the year 2001, CNES proposed through the ANGEL phase 1 programme to preprare the required technical maturity before that RLV's become alternatives to ELV's. In such way, system ,propulsion, ground based demonstrations, aero-thermo-dynamics as well as in flight experimentation are planned. This paper is focused on the aero-thermo-dynamics (ATD) and in flight demonstration activities with emphasis on the better understanding of ATD problems emerging from past programmes among them shock wave transitionnal boundary layer interaction on surface control, boundary layer transition, local aerothermodynamic effects, gas- surface interaction, catalycity, base flow prediction,...In order to minimize as small as possible the management risk a first generation of vehicle dubbed Pre_X is designed to validate technological choices and to have as soon as possible re-entry data to calibrate the various tools involved in the future RLV definition. In addition, the main requirement for PRE_X aeroshape definition and the two different design approaches considered by Dassault Aviation and EADS-LV are discussed. Then, the more promising concept for the PRE_X application is presented. Finally, the current status of the ATD activities is given as well as the perspectives.

Preliminar modelling of the chemical impact of possible TLEs on the lower ionosphere of Saturn

NASA Astrophysics Data System (ADS)

Gordillo-Vazquez, F. J.; Luque, A.; Dubrovin, D.; Yair, Y.; Price, C.

2013-09-01

Lightning on Saturn has been confirmed by radio [1] and optical signal observations [2]. On Earth, lightning activity is accompanied by a diversity of Transient Luminous Events (TLEs) above the thunder clouds in the stratosphere, where crawlers and blue jets take place, and in the mesosphere where elves, sprites, halos and giant blue jets occur. Optical emissions from TLEs are produced by electric breakdown in the mesosphere (50 - 90 km) due to the field generated by the electric charges accumulated in the trophospheric thunder clouds. The existence of powerful lightning on Saturn might produce, as on Earth, elves and other TLE phenomena in the lower ionosphere of Saturn [3]. We have developed a preliminar time-dependent kinetic model to account for the possible chemical disturbances of halo-like TLEs in the night-time mid-latitude H2/He atmosphere of Saturn. In particular, we have quantified the variation of electron and ion densities at different altitudes (650 - 1000 km) above the 1 bar level together with an estimation of the photon emissions associated to the radiative decays of some excited electronic levels of H2 like H2(d3Πu) responsible for the Fulcher bands in the blue optical range and H2(a3Σ+g) that radiatively decays producing ultraviolet blue continuum emission.

GN and C Subsystem Concept for Safe Precision Landing of the Proposed Lunar MARE Robotic Science Mission

NASA Technical Reports Server (NTRS)

Carson, John M., III; Johnson, Andrew E.; Anderson, F. Scott; Condon, Gerald L.; Nguyen, Louis H.; Olansen, Jon B.; Devolites, Jennifer L.; Harris, William J.; Hines, Glenn D.; Lee, David E.;

Defining contamination control requirements for non-human research on Space Station Freedom

NASA Technical Reports Server (NTRS)

Corbin, Barbara J.; Funk, Glenn A.

1992-01-01

The use of non-human biological specimens for life sciences research on Space Station Freedom has generated concerns about spacecraft internal contamination, crew safety and hardware utility. Various NASA organizations convened to discuss the concerns and determine how they should be addressed. This paper will present the issues raised at this meeting, the process by which safety concerns were identified, and the means by which contamination control requirements for all biological payloads were recommended for incorporation into Space Station Freedom safety requirements. The microbiological, toxicological and particulate contamination criteria for long-term spaceflight will be based on realistic assessment of risk and hardware will be designed to meet established contamination criteria while facilitating crew operations, thereby meeting the needs of the investigator.

The NASA Aerospace Battery Safety Handbook

NASA Technical Reports Server (NTRS)

Halpert, Gerald; Subbarao, Surampudi; Rowlette, John J.

1986-01-01

This handbook has been written for the purpose of acquainting those involved with batteries with the information necessary for the safe handling, storage, and disposal of these energy storage devices. Included in the document is a discussion of the cell and battery design considerations and the role of the components within a cell. The cell and battery hazards are related to user- and/or manufacturer-induced causes. The Johnson Space Center (JSC) Payload Safety Guidelines for battery use in Shuttle applications are also provided. The electrochemical systems are divided into zinc anode and lithium anode primaries, secondary cells, and fuel cells. Each system is briefly described, typical applications are given, advantages and disadvantages are tabulated, and most importantly, safety hazards associated with its use are given.

KSC-03PP-0149

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, who represents the Israel Space Agency, chats with the Closeout Crew in the White Room before entering Columbia. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Ramon is the first Israeli astronaut to fly in the Shuttle. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

KSC-03pp0149

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, who represents the Israel Space Agency, chats with the Closeout Crew in the White Room before entering Columbia. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Ramon is the first Israeli astronaut to fly in the Shuttle. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

Impact of low gravity on water electrolysis operation

NASA Technical Reports Server (NTRS)

Powell, F. T.; Schubert, F. H.; Lee, M. G.

1989-01-01

Advanced space missions will require oxygen and hydrogen utilities for several important operations including the following: (1) propulsion; (2) electrical power generation and storage; (3) environmental control and life support; (4) extravehicular activity; (5) in-space manufacturing and (6) in-space science activities. An experiment suited to a Space Shuttle standard middeck payload has been designed for the Static Feed Water Electrolysis technology which has been viewed as being capable of efficient, reliable oxygen and hydrogen generation with few subsystem components. The program included: end use design requirements, phenomena to be studied, Space Shuttle Orbiter experiment constraints, experiment design and data requirements, and test hardware requirements. The objectives are to obtain scientific and engineering data for future research and development and to focus on demonstrating and monitoring for safety of a standard middeck payload.

KSC-02pd1938

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- -- The STS-107 crew poses for a group portrait with their instructor beside an M113 armored personnel carrier. The crew is participating in Terminal Countdown Demonstration Test activities, a standard part of launch preparations. In the front, from left, are Payload Specialist Ilan Ramon (the first Israeli astronaut), Instructor George Hoggard, Mission Specialist Laurel Clark, Commander Rick Husband, Mission Specialist David Brown, and Payload Commander Michael Anderson. In the back, from left, are Mission Specialist Kalpana Chawla and Pilot William "Willie" McCool. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

STS-107 crew meet with media in front of grandstand at KSC

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- The STS-107 crew meet with the media in front of the grandstand. With the microphone is Payload Specialist Ilan Ramon, the first Israeli astronaut. Others, from left, are Commander Rick Husband, Pilot William 'Willie' McCool, Ramon, Mission Specialist David Brown, Payload Commander Michael Anderson, and Mission Specialists Laurel Clark and Kalpana Chawla. The crew just finished Terminal Countdown Demonstration Test activities, including a simulated launch countdown, in preparation for launch planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. .

Analysis of nuclear waste disposal in space, phase 3. Volume 1: Executive summary of technical report

NASA Technical Reports Server (NTRS)

Rice, E. E.; Miller, N. E.; Yates, K. R.; Martin, W. E.; Friedlander, A. L.

1980-01-01

The objectives, approach, assumptions, and limitations of a study of nuclear waste disposal in space are discussed with emphasis on the following: (1) payload characterization; (2) safety assessment; (3) health effects assessment; (4) long-term risk assessment; and (5) program planning support to NASA and DOE. Conclusions are presented for each task.

Unmanned Aerial Vehicles

DTIC Science & Technology

1994-05-31

Project , which is part of the trol, Communications and Intelligence In response to congressional...direction in Program Executive Office, Cruise Mis- (C31), the working group includes repre- FY88 to consolidate the management of siles Project and Unmanned...34* Support test and evaluation of ated with the draw down of the Pioneer Invest selectively in safety potential UAV payloads system as it is replaced by the

NASA's Advanced solid rocket motor

NASA Technical Reports Server (NTRS)

Mitchell, Royce E.

1993-01-01

The Advanced Solid Rocket Motor (ASRM) will not only bring increased safety, reliability and performance for the Space Shuttle Booster, it will enhance overall Shuttle safety by effectively eliminating 174 failure points in the Space Shuttle Main Engine throttling system and by reducing the exposure time to aborts due to main engine loss or shutdown. In some missions, the vulnerability time to Return-to-Launch Site aborts is halved. The ASRM uses case joints which will close or remain static under the effects of motor ignition and pressurization. The case itself is constructed of the weldable steel alloy HP 9-4-0.30, having very high strength and with superior fracture toughness and stress corrosion resistance. The internal insulation is strip-wound and is free of asbestos. The nozzle employs light weight ablative parts and is some 5,000 pounds lighter than the Shuttle motor used to date. The payload performance of the ASRM-powered Shuttle is 12,000 pounds higher than that provided by the present motor. This is of particular benefit for payloads delivered to higher inclinations and/or altitudes. The ASRM facility uses state-of-the-art manufacturing techniques, including continuous propellant mixing and direct casting.

Case Studies in Crewed Spacecraft Environmental Control and Life Support System Process Compatibility and Cabin Environmental Impact

NASA Technical Reports Server (NTRS)

Perry, J. L.

2017-01-01

Contamination of a crewed spacecraft's cabin environment leading to environmental control and life support system (ECLSS) functional capability and operational margin degradation or loss can have an adverse effect on NASA's space exploration mission figures of merit-safety, mission success, effectiveness, and affordability. The role of evaluating the ECLSS's compatibility and cabin environmental impact as a key component of pass trace contaminant control is presented and the technical approach is described in the context of implementing NASA's safety and mission success objectives. Assessment examples are presented for a variety of chemicals used in vehicle systems and experiment hardware for the International Space Station program. The ECLSS compatibility and cabin environmental impact assessment approach, which can be applied to any crewed spacecraft development and operational effort, can provide guidance to crewed spacecraft system and payload developers relative to design criteria assigned ECLSS compatibility and cabin environmental impact ratings can be used by payload and system developers as criteria for ensuring adequate physical and operational containment. In additional to serving as an aid for guiding containment design, the assessments can guide flight rule and procedure development toward protecting the ECLSS as well as approaches for contamination event remediation.

NH11B-1726: FrankenRaven: A New Platform for Remote Sensing

NASA Technical Reports Server (NTRS)

Dahlgren, Robert; Fladeland, Matthew M.; Pinsker, Ethan A.; Jasionowicz, John P.; Jones, Lowell L.; Pscheid, Matthew J.

2016-01-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into FrankenRaven aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

FrankenRaven: A New Platform for Remote Sensing

NASA Astrophysics Data System (ADS)

Dahlgren, R. P.; Fladeland, M. M.; Pinsker, E. A.; Jasionowicz, J. P.; Jones, L. L.; Mosser, C. D.; Pscheid, M. J.; Weidow, N. L.; Kelly, P. J.; Kern, C.; Werner, C. A.; Johnson, M. S.

2016-12-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into "FrankenRaven" aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

Norton-Thevenin Receptance Coupling (NTRC) as a Payload Design Tool

NASA Technical Reports Server (NTRS)

Gordon, Scott; Kaufman, Dan; Majed, Arya

2017-01-01

The NASA Engineering and Safety Center (NESC) is funding a study to develop an alternate method for performing coupled loads analysis called Norton-Thevenin Receptance Coupling (NTRC). NTRC combines Receptance Coupling (RC), a frequency-domain synthesis method and Norton-Thevenin (NT) theory, an impedance based approach for simulating the interaction between dynamic systems. The goal of developing the NTRC method is to provide a tool that payload developers can use to reduce the conservatism in defining preliminary design loads, assess the impact of design changes between formal load cycles, and to perform trade studies for design optimization with a minimum amount of data required from the launch vehicle (LV) provider. NTRC also has the ability to perform parametric loads analysis where many different design configurations can be evaluated. This will result in cost and schedule benefits to the payload developer that are currently not possible under the standard coupled loads analysis (CLA) flow where typically only 2-3 official load cycles are performed by the LV provider over the life of a payload program. NTRC is not envisioned as a replacement for the official load cycles performed by the LV provider but rather as a means to address the types of design issues faced by the payload developer before and between official load cycles.The presentation provides an overview of the NTRC methodology and discusses how NTRC can be used to replicate the results from a standard LV CLA. The presentation covers the benchmarking that has been performed as part of the NESC study to demonstrate the accuracy of the technique for both frequency and time domain dynamic analyses. Future plans for benchmarking the NTRC approach against CLA results for NASAs Space Launch System (SLS) and commercial launch vehicles are discussed and the role that NTRC is envisioned to play in the payload development cycle.

Developments in Quantitative Structure-Activity Relationships (QSAR). A Review

DTIC Science & Technology

1976-07-01

hyphae Analogs Inhibition of s-Nitrostyrenes 20 84 Growth Botrytie -,inerea Inhibition of a-Nitrostyrenes 6 84 Grcwth Bovine hemoglobin Binding of...AspergiL us niger, phenyl methacrylates upon Ranse-nula awmat~a and RR’NCSS Na+ upon Botrytis cinerea conformed to the general equation 35. The equations...log II vs log kw *79 Botrytis cinerea , 41, 64 -lg! slgý,7 Bovine hemoglobin, 36 lg Elv o .,7 Bovine serum albumin, 36 - log iI vs log P, 79 - log JE

Space Station Freedom altitude strategy

NASA Technical Reports Server (NTRS)

Mcdonald, Brian M.; Teplitz, Scott B.

1990-01-01

The Space Station Freedom (SSF) altitude strategy provides guidelines and assumptions to determine an altitude profile for Freedom. The process for determining an altitude profile incorporates several factors such as where the Space Shuttle will rendezvous with the SSF, when reboosts must occur, and what atmospheric conditions exist causing decay. The altitude strategy has an influence on all areas of SSF development and mission planning. The altitude strategy directly affects the micro-gravity environment for experiments, propulsion and control system sizing, and Space Shuttle delivery manifests. Indirectly the altitude strategy influences almost every system and operation within the Space Station Program. Evolution of the SSF altitude strategy has been a very dynamic process over the past few years. Each altitude strategy in turn has emphasized a different consideration. Examples include a constant Space Shuttle rendezvous altitude for mission planning simplicity, or constant micro-gravity levels with its inherent emphasis on payloads, or lifetime altitudes to provide a safety buffer to loss of control conditions. Currently a new altitude strategy is in development. This altitude strategy will emphasize Space Shuttle delivery optimization. Since propellant is counted against Space Shuttle payload-to-orbit capacity, lowering the rendezvous altitude will not always increase the net payload-to-orbit, since more propellant would be required for reboost. This altitude strategy will also consider altitude biases to account for Space Shuttle launch slips and an unexpected worsening of atmospheric conditions. Safety concerns will define a lower operational altitude limit, while radiation levels will define upper altitude constraints. The evolution of past and current SSF altitude strategies and the development of a new altitude strategy which focuses on operational issues as opposed to design are discussed.

Endovenous laser ablation of varicose perforating veins with the 1470-nm diode laser using the radial fibre slim.

PubMed

Zerweck, Christof; von Hodenberg, Eva; Knittel, Matthias; Zeller, Thomas; Schwarz, Thomas

2014-02-01

Endovenous Laser Ablation (EVLA) is one of the most accepted treatment options for varicose veins. The aim of this study was to investigate the efficacy and safety of the new radial fiber slim (ELVeS-radial-slim kit™) for the 1470 nm diode laser in perforator veins with a 1 month follow-up. Our prospective observational cohort study comprised 69 perforating veins in 55 patients. Ninety percent of all patients were in the CEAP-stage C3-C6. The radial fiber slim was used to occlude the perforating vein and the great or small saphenous vein in the same procedure. The primary efficacy endpoint of the study was ultrasonographically proven elimination of venous reflux in the perforating vein after at least one month. Secondary efficacy and further safety end points after one month were as follows: (1) sonographic exclusion of recanalization of the treated vein segments, (2) deep vein thrombosis (DVT), clinical pulmonary embolism (PE), or superficial vein thrombosis (SVT) as defined by objective testing, (3) death from any cause, (4) persistent clinical complaints such as pain and paresthesia. Follow-up could be completed in all patients. In all treated perforating varicose veins, occlusion with elimination of reflux could be demonstrated immediately after the procedure. After one month 95.6% of the treated veins were still occluded (67/69). During follow-up, we did not diagnose any DVT, PE or SVT in the area related to the treated perforating vein. No patient died. One patient reported paresthesia distally of the puncture site. Endovenous laser treatment of varicose perforating veins with 1470 nm diode laser using the radial fiber slim is effective and safe with low recanalization rates during 1-month follow-up.

NASA Flight Operations of Ikhana and Global Hawk

NASA Technical Reports Server (NTRS)

Posada, Herman D.

2009-01-01

This viewgraph presentation reviews the flight operations of Ikhana and Global Hawk Fire missions. The Ikhana fire missions modifications, ground systems, flight operations, range safety zones, primary and secondary emergency landing sites, and the Ikhana western states fire missions of 2007 are described, along with The Global Hawk specs, a description of the Global Hawk Pacific Science Campaign (GloPac '09) and GloPac payloads.

Orbit Transfer Vehicle (OTV) engine, phase A study. Volume 2: Study

NASA Technical Reports Server (NTRS)

Mellish, J. A.

1979-01-01

The hydrogen oxygen engine used in the orbiter transfer vehicle is described. The engine design is analyzed and minimum engine performance and man rating requirements are discussed. Reliability and safety analysis test results are presented and payload, risk and cost, and engine installation parameters are defined. Engine tests were performed including performance analysis, structural analysis, thermal analysis, turbomachinery analysis, controls analysis, and cycle analysis.

Capabilities-Based Planning for Energy Security at Department of Defense Installations

DTIC Science & Technology

2013-01-01

Support Services—The ability to provide assis- tance for payload and launch vehicles including safety, reception , staging, integration, movement to the...pubs/technical_reports/TR1249.html Davis, Paul K., and Paul Dreyer, RAND’s Portfolio Analysis Tool (PAT): Theory , Methods, and Reference Manual, Santa...Steven C. Bankes, and Michael Egner, Enhancing Strategic Planning with Massive Scenario Generation: Theory and Experiments, Santa Monica, Calif

ASAP members view LVSA and Orion Stage Adapter

NASA Image and Video Library

2018-03-12

ASAP, (Aerospace Safety Advisory Panel), members, Dr. Sandra Magnus, Dr. Donald P. McErlean, Dr. George Nield, Captain Christopher Saindon, Mr. David West, Dr. Patricia Sanders, Ms. Carol Hamilton, Ms. Evette Whatley, Ms. Paula Frankel, view LVSA, (Launch Vehicle Stage Adapter), and Orion Stage Adapter. Members were escorted to buildings 4707 and 4708 by Andrew Schorr, Deputy Manager for Spacecraft/Payload Integration & Evolution Office (SPIE)

A Study of the Economic Benefit Potential of Intermodal Transports

NASA Technical Reports Server (NTRS)

Nelson, J. M.; Kawai, R. T.; Gregg, R. D.; McKinley, Robert E., Jr. (Technical Monitor)

2001-01-01

A conceptual study was conducted to determine the benefit potential of an Intermodal Transport in which quick change payload modules are used to reduce the cost of air travel by increasing daily utilization. Three basic concepts varying the degree of modularity were investigated for a 122,000 pounds payload 3,000 NM range regional wide body transport. The profit potential for operating as a passenger transport during the day and as a freighter at night was assessed. Assuming current levels of profitability, Intermodal operations could offer an operating cost reduction potential up to 20%. Enabling technology needs are identified as very quiet aircraft for expanded night operations, distributed load carrying quick disconnect latching, and configuration dependent safety issues. Recommendations are made to explore if additional benefits are possible from alternative mission and usage modules.

STS-107 crew poses for a group portrait with their instructor inside an M113

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- The STS-107 crew poses for a group portrait with their instructor inside an M113 armored personnel carrier. The crew is participating in Terminal Countdown Demonstration Test activities, a standard part of launch preparations. From left to right are Pilot William 'Willie' McCool, Commander Rick Husband, Mission Specialist Laurel Clark, Instructor George Hoggard, Mission Specialist Kalpana Chawla, Payload Specialist Ilan Ramon (the first Israeli astronaut), Payload Commander Michael Anderson, and Mission Specialist David Brown. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

The History of Venting (part I)

NASA Technical Reports Server (NTRS)

Leiter, Stephen C.

2017-01-01

Venting techniques and design are an important implementation strategy for observatory and payload contamination control, and yet venting analysis has seen a topsey turvey history, at lease from the perspective of the simple Layman trying to design a black box. Additionally, designing the vent has competing controls from Safety and EMIEMC. In the days of Shuttle, Safety placed liens against the vents of blankets, boxes, and large structural items principally to protect cargo bay vents but also from a flammability perspective. What continues to elude the Designer Community is a stable, simple way of designing vents for black boxes that satisfies everybody. But we continue to try.

STS-99 crew talk to media near launch pad

NASA Technical Reports Server (NTRS)

2000-01-01

The STS-99 crew take time out during Terminal Countdown Demonstration Test (TCDT) activities to talk to the media. From left to right are Commander Kevin Kregel, Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

NASA's Space Launch System Program Update

NASA Technical Reports Server (NTRS)

May, Todd; Lyles, Garry

2015-01-01

Hardware and software for the world's most powerful launch vehicle for exploration is being welded, assembled, and tested today in high bays, clean rooms and test stands across the United States. NASA's Space Launch System (SLS) continued to make significant progress in the past year, including firing tests of both main propulsion elements, manufacturing of flight hardware, and the program Critical Design Review (CDR). Developed with the goals of safety, affordability, and sustainability, SLS will deliver unmatched capability for human and robotic exploration. The initial Block 1 configuration will deliver more than 70 metric tons (t) (154,000 pounds) of payload to low Earth orbit (LEO). The evolved Block 2 design will deliver some 130 t (286,000 pounds) to LEO. Both designs offer enormous opportunity and flexibility for larger payloads, simplifying payload design as well as ground and on-orbit operations, shortening interplanetary transit times, and decreasing overall mission risk. Over the past year, every vehicle element has manufactured or tested hardware, including flight hardware for Exploration Mission 1 (EM-1). This paper will provide an overview of the progress made over the past year and provide a glimpse of upcoming milestones on the way to a 2018 launch readiness date.

KSC00pp0042

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- The STS-99 crew take time out during Terminal Countdown Demonstration Test (TCDT) activities to talk to the media. From left to right are Commander Kevin Kregel, Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. ES

KSC-00pp0014

NASA Image and Video Library

2000-01-12

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Mission Specialist Gerhard Thiele, who is with the European Space Agency, is ready to practice driving an armored personnel carrier that is part of emergency egress training and could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0009

NASA Image and Video Library

2000-01-11

The STS-99 crew pose for a photo after their arrival at KSC's Shuttle Landing Facility. From left are Mission Specialists Gerhard Thiele, and Janice Voss (Ph.D.), Commander Kevin Kregel, Mission Specialists Janet Lynn Kavandi (Ph.D.) and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0003

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Gerhard Thiele, with the European Space Agency, arrives at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), and Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0005

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Janet Lynn Kavandi (Ph.D.) smiles on her arrival at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janice Voss (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, and Gerhard Thiele, with the European Space Agency. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0020

NASA Image and Video Library

2000-01-12

Under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, STS-99 Commander Kevin Kregel practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0012

NASA Image and Video Library

2000-01-12

STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, smiles during training on the M-113, an armored personnel carrier that is part of emergency egress training during Terminal Countdown Demonstration Test (TCDT) activities. The tracked vehicle could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0020

NASA Image and Video Library

2000-01-12

Under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, STS-99 Commander Kevin Kregel practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0005

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Janet Lynn Kavandi (Ph.D.) smiles on her arrival at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janice Voss (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, and Gerhard Thiele, with the European Space Agency. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0042

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- The STS-99 crew take time out during Terminal Countdown Demonstration Test (TCDT) activities to talk to the media. From left to right are Commander Kevin Kregel, Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. ES

KSC00pp0003

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Gerhard Thiele, with the European Space Agency, arrives at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic Gorie, and Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), and Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0015

NASA Image and Video Library

2000-01-12

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Pilot Dominic Gorie , is ready to practice driving an armored personnel carrier that is part of emergency egress training and could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Behind him (left) is Mission Specialist Gerhard Thiele, who is with the European Space Agency. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0048

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- Near the bunker at Launch Pad 39A, STS-99 Mission Specialists Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri check out the slidewire basket used for emergency egress. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

Hardware interface for isolation of vibrations in flexible manipulators: Development and applications

NASA Technical Reports Server (NTRS)

Manouchehri, Davoud; Lindsay, Thomas; Ghosh, David

1994-01-01

NASA's Langley Research Center (LaRC) is addressing the problem of isolating the vibrations of the Shuttle remote manipulator system (RMS) from its end-effector and/or payload by modeling an RMS flat-floor simulator with a dynamic payload. Analysis of the model can lead to control techniques that will improve the speed, accuracy, and safety of the RMS in capturing satellites and eventually facilitate berthing with the space station. Rockwell International Corporation, also involved in vibration isolation, has developed a hardware interface unit to isolate the end-effector from the vibrations of an arm on a Shuttle robotic tile processing system (RTPS). To apply the RTPS isolation techniques to long-reach arms like the RMS, engineers have modeled the dynamics of the hardware interface unit with simulation software. By integrating the Rockwell interface model with the NASA LaRC RMS simulator model, investigators can study the use of a hardware interface to isolate dynamic payloads from the RMS. The interface unit uses both active and passive compliance and damping for vibration isolation. Thus equipped, the RMS could be used as a telemanipulator with control characteristics for capture and berthing operations. The hardware interface also has applications in industry.

KSC-00pp0017

NASA Image and Video Library

2000-01-12

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Mission Specialist Janice Voss (Ph.D.) is ready to practice driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. In the rear (right) is Commander Kevin Kregel. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Commander Kevin Kregel is ready to practice driving the M- 113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Mission Specialist Janet Lynn Kavandi (Ph.D.) is ready to practice driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M- 113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station- derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Mission Specialist Gerhard Thiele, who is with the European Space Agency, is ready to practice driving an armored personnel carrier that is part of emergency egress training and could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

Under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, STS-99 Commander Kevin Kregel practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

Multivalent peptidic linker enables identification of preferred sites of conjugation for a potent thialanstatin antibody drug conjugate.

PubMed

Puthenveetil, Sujiet; He, Haiyin; Loganzo, Frank; Musto, Sylvia; Teske, Jesse; Green, Michael; Tan, Xingzhi; Hosselet, Christine; Lucas, Judy; Tumey, L Nathan; Sapra, Puja; Subramanyam, Chakrapani; O'Donnell, Christopher J; Graziani, Edmund I

2017-01-01

Antibody drug conjugates (ADCs) are no longer an unknown entity in the field of cancer therapy with the success of marketed ADCs like ADCETRIS and KADCYLA and numerous others advancing through clinical trials. The pursuit of novel cytotoxic payloads beyond the mictotubule inhibitors and DNA damaging agents has led us to the recent discovery of an mRNA splicing inhibitor, thailanstatin, as a potent ADC payload. In our previous work, we observed that the potency of this payload was uniquely tied to the method of conjugation, with lysine conjugates showing much superior potency as compared to cysteine conjugates. However, the ADC field is rapidly shifting towards site-specific ADCs due to their advantages in manufacturability, characterization and safety. In this work we report the identification of a highly efficacious site-specific thailanstatin ADC. The site of conjugation played a critical role on both the in vitro and in vivo potency of these ADCs. During the course of this study, we developed a novel methodology of loading a single site with multiple payloads using an in situ generated multi-drug carrying peptidic linker that allowed us to rapidly screen for optimal conjugation sites. Using this methodology, we were able to identify a double-cysteine mutant ADC delivering four-loaded thailanstatin that was very efficacious in a gastric cancer xenograft model at 3mg/kg and was also shown to be efficacious against T-DM1 resistant and MDR1 overexpressing tumor cell lines.

Aeronautics and Space Report of the President, Fiscal Year 2002 Activities

NASA Technical Reports Server (NTRS)

2002-01-01

Fiscal Year (FY) 2002 brought advances on many fronts in support of NASAs new vision, announced by Administrator Sean OKeefe on April 12, to improve life here, to extend life to there, to find life beyond. NASA successfully carried out four Space Shuttle missions, including three to the International Space Station (ISS) and one servicing mission to the Hubble Space Telescope (HST). By the end of the fiscal year, humans had occupied the ISS continuously for 2 years. NASA also managed five expendable launch vehicle (ELV) missions and participated in eight international cooperative ELV launches. In the area of space science, two of the Great Observatories, the Hubble Space Telescope and the Chandra X-Ray Observatory, continued to make spectacular observations. The Mars Global Surveyor and Mars Odyssey carried out their mapping missions of the red planet in unprecedented detail. Among other achievements, the Near Earth Asteroid Rendezvous (NEAR) Shoemaker spacecraft made the first soft landing on an asteroid, and the Solar and Heliospheric Observatory (SOHO) monitored a variety of solar activity, including the largest sunspot observed in 10 years. The education and public outreach program stemming from NASAs space science missions continues to grow. In the area of Earth science, attention focused on completing the first Earth Observing Satellite series. Four spacecraft were successfully launched. The goal is to understand our home planet as a system, as well as how the global environment responds to change.

Feasibility Study on S-Band Microwave Radiation and 3D-Thermal Infrared Imaging Sensor-Aided Recognition of Polymer Materials from End-of-Life Vehicles

PubMed Central

Huang, Jiu; Zhu, Zhuangzhuang; Tian, Chuyuan; Bian, Zhengfu

2018-01-01

With the increase the worldwide consumption of vehicles, end-of-life vehicles (ELVs) have kept rapidly increasing in the last two decades. Metallic parts and materials of ELVs can be easily reused and recycled, but the automobile shredder residues (ASRs), of which elastomer and plastic materials make up the vast majority, are difficult to recycle. ASRs are classified as hazardous materials in the main industrial countries, and are required to be materially recycled up to 85–95% by mass until 2020. However, there is neither sufficient theoretical nor practical experience for sorting ASR polymers. In this research, we provide a novel method by using S-Band microwave irradiation together with 3D scanning as well as infrared thermal imaging sensors for the recognition and sorting of typical plastics and elastomers from the ASR mixture. In this study, an industrial magnetron array with 2.45 GHz irradiation was utilized as the microwave source. Seven kinds of ELV polymer (PVC, ABS, PP, EPDM, NBR, CR, and SBR) crushed scrap residues were tested. After specific power microwave irradiation for a certain time, the tested polymer materials were heated up to different extents corresponding to their respective sensitivities to microwave irradiation. Due to the variations in polymer chemical structure and additive agents, polymers have different sensitivities to microwave radiation, which leads to differences in temperature rises. The differences of temperature increase were obtained by a thermal infrared sensor, and the position and geometrical features of the tested scraps were acquired by a 3D imaging sensor. With this information, the scrap material could be recognized and then sorted. The results showed that this method was effective when the tested polymer materials were heated up to more than 30 °C. For full recognition of the tested polymer scraps, the minimum temperature variations of 5 °C and 10.5 °C for plastics and elastomers were needed, respectively. The sorting efficiency was independent of particle sizes but depended on the power and time of the microwave irradiation. Generally, more than 75% (mass) of the tested polymer materials could be successfully recognized and sorted under an irradiation power of 3 kW. Plastics were much more insensitive to microwave irradiation than elastomers. With this method, the tested mixture of the plastic group (PVC, ABS, PP) and the mixture of elastomer group (EPDM, NBR, CR, and SBR) could be fully separated with an efficiency of 100%. PMID:29702564

Feasibility Study on S-Band Microwave Radiation and 3D-Thermal Infrared Imaging Sensor-Aided Recognition of Polymer Materials from End-of-Life Vehicles.

PubMed

Huang, Jiu; Zhu, Zhuangzhuang; Tian, Chuyuan; Bian, Zhengfu

2018-04-27

With the increase the worldwide consumption of vehicles, end-of-life vehicles (ELVs) have kept rapidly increasing in the last two decades. Metallic parts and materials of ELVs can be easily reused and recycled, but the automobile shredder residues (ASRs), of which elastomer and plastic materials make up the vast majority, are difficult to recycle. ASRs are classified as hazardous materials in the main industrial countries, and are required to be materially recycled up to 85⁻95% by mass until 2020. However, there is neither sufficient theoretical nor practical experience for sorting ASR polymers. In this research, we provide a novel method by using S-Band microwave irradiation together with 3D scanning as well as infrared thermal imaging sensors for the recognition and sorting of typical plastics and elastomers from the ASR mixture. In this study, an industrial magnetron array with 2.45 GHz irradiation was utilized as the microwave source. Seven kinds of ELV polymer (PVC, ABS, PP, EPDM, NBR, CR, and SBR) crushed scrap residues were tested. After specific power microwave irradiation for a certain time, the tested polymer materials were heated up to different extents corresponding to their respective sensitivities to microwave irradiation. Due to the variations in polymer chemical structure and additive agents, polymers have different sensitivities to microwave radiation, which leads to differences in temperature rises. The differences of temperature increase were obtained by a thermal infrared sensor, and the position and geometrical features of the tested scraps were acquired by a 3D imaging sensor. With this information, the scrap material could be recognized and then sorted. The results showed that this method was effective when the tested polymer materials were heated up to more than 30 °C. For full recognition of the tested polymer scraps, the minimum temperature variations of 5 °C and 10.5 °C for plastics and elastomers were needed, respectively. The sorting efficiency was independent of particle sizes but depended on the power and time of the microwave irradiation. Generally, more than 75% (mass) of the tested polymer materials could be successfully recognized and sorted under an irradiation power of 3 kW. Plastics were much more insensitive to microwave irradiation than elastomers. With this method, the tested mixture of the plastic group (PVC, ABS, PP) and the mixture of elastomer group (EPDM, NBR, CR, and SBR) could be fully separated with an efficiency of 100%.

Aerodynamic Control-Augmentation Devices For Saturn-Class Launch Vehicles With Aft Centers Of Gravity

NASA Technical Reports Server (NTRS)

Barret, Chris

1995-01-01

Report describes study of aerodynamic flight-control-augmentation devices proposed for use in increasing payload capabilities of future launch vehicles by allowing more aft centers of gravity. Proposed all-movable devices not only provide increased control authority during ascent trajectory, but also reduce engine gimballing requirements and enhance crew safety. Report proposes various aerodynamic control surfaces mounted fore and aft on Saturn-class launch vehicle.

D-X Payload Ready For Flight

NASA Image and Video Library

2017-12-08

Matthew Mullin and Bobby Meazell, Orbital ATK/Columbia Scientific Balloon Facility technicians, conduct compatibility testing on NASA Langley Research Center’s Radiation Dosimetry Experiment payload Wednesday, Sept. 9, at Fort Sumner, N.M. The successful compatibility test was a key milestone in ensuring the flight readiness of RaD-X, which is scheduled to launch on an 11-million-cubic-foot NASA scientific balloon no earlier than Friday, Sept. 11, from the agency’s balloon launching facility in Fort Sumner. RaD-X will measure cosmic ray energy at two separate altitude regions in the stratosphere—above 110,000 feet and between 69,000 to 88,500 feet. The data is key to confirming Langley’s Nowcast of Atmospheric Ionizing Radiation for Aviation Safety (NAIRAS) model, which is a physics-based model that determines solar radiation and galactic cosmic ray exposure globally in real-time. The NAIRAS modeling tool will be used to help enhance aircraft safety as well as safety procedures for the International Space Station. In addition to the primary payload, 100 small student experiments will fly on the RaD-X mission as part of the Cubes in Space program. The program provides 11- to 18-year-old middle and high school students a no-cost opportunity to design and compete to launch an experiment into space or into the near-space environment. The cubes measure just 4 centimeters by 4 centimeters. NASA’s scientific balloons offer low-cost, near-space access for scientific payloads weighing up to 8,000 pounds for conducting scientific investigations in fields such as astrophysics, heliophysics and atmospheric research. NASA’s Wallops Flight Facility in Virginia manages the agency’s scientific balloon program with 10 to 15 flights each year from launch sites worldwide. Orbital ATK provides program management, mission planning, engineering services and field operations for NASA’s scientific balloon program. The program is executed from the Columbia Scientific Balloon Facility in Palestine, Texas. The Columbia team has launched more than 1,700 scientific balloons in over 35 years of operation. Anyone may track the progress of the Fort Sumner flights, which includes a map showing the balloon’s real-time location, at: towerfts.csbf.nasa.gov/ For more information on the balloon program, see: www.nasa.gov/scientificballoons NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Micro-aerial vehicle type wall-climbing robot mechanism for structural health monitoring

NASA Astrophysics Data System (ADS)

Shin, Jae-Uk; Kim, Donghoon; Kim, Jong-Heon; Myung, Hyun

2013-04-01

Currently, the maintenance or inspection of large structures is labor-intensive, so it has a problem of the large cost due to the staffing professionals and the risk for hard to reach areas. To solve the problem, the needs of wall-climbing robot are emerged. Infra-based wall-climbing robots to maintain an outer wall of building have high payload and safety. However, the infrastructure for the robot must be equipped on the target structure and the infrastructure isn't preferred by the architects since it can injure the exterior of the structure. These are the reasons of why the infra-based wall-climbing robot is avoided. In case of the non-infra-based wall-climbing robot, it is researched to overcome the aforementioned problems. However, most of the technologies are in the laboratory level since the payload, safety and maneuverability are not satisfactory. For this reason, aerial vehicle type wall-climbing robot is researched. It is a flying possible wallclimbing robot based on a quadrotor. It is a famous aerial vehicle robot using four rotors to make a thrust for flying. This wall-climbing robot can stick to a vertical wall using the thrust. After sticking to the wall, it can move with four wheels installed on the robot. As a result, it has high maneuverability and safety since it can restore the position to the wall even if it is detached from the wall by unexpected disturbance while climbing the wall. The feasibility of the main concept was verified through simulations and experiments using a prototype.

Pressure fed thrust chamber technology program

NASA Technical Reports Server (NTRS)

Dunn, Glen M.

1992-01-01

This is the final report for the Pressure Fed Technology Program. It details the design, fabrication, and testing of subscale hardware which successfully characterized Liquid Oxygen Rocket Propulsion (LOX/RP) combustion for low cost pressure fed design. The innovative modular injector design is described in detail as well as hot-fire test results which showed excellent performance. The program summary identifies critical LOX/RP design issues that have been resolved in this testing, and details the low risk development requirements for low cost engines for future Expandable Launch Vehicles (ELV).

An Overview of the Microgravity Science Glovebox (MSG) Facility and the Research Performed in the MSG on the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Jordan, Lee P.

2013-01-01

The Microgravity Science Glovebox (MSG) is a rack facility aboard the International Space Station (ISS) designed for investigation handling. The MSG was built by the European Space Agency (ESA) which also provides sustaining engineering support for the facility. The MSG has been operating on the ISS since July 2002 and is currently located in the US Laboratory Module. The unique design of the facility allows it to accommodate science and technology investigations in a "workbench" type environment. The facility has an enclosed working volume that is held at a negative pressure with respect to the crew living area. This allows the facility to provide two levels of containment for small parts, particulates, fluids, and gases. This containment approach protects the crew from possible hazardous operations that take place inside the MSG work volume. Research investigations operating inside the MSG are provided a large 255 liter enclosed work space, 1000 watts of dc power via a versatile supply interface (120, 28, +/- 12, and 5 Vdc), 1000 watts of cooling capability, video and data recording and real time downlink, ground commanding capabilities, access to ISS Vacuum Exhaust and Vacuum Resource Systems, and gaseous nitrogen supply. These capabilities make the MSG one of the most utilized facilities on ISS. The MSG has been used for over 14500 hours of scientific payload operations. MSG investigations involve research in cryogenic fluid management, fluid physics, spacecraft fire safety, materials science, combustion, plant growth, and life support technology. The MSG facility is operated by the Payloads Operations Integration Center at Marshall Space flight Center. Payloads may also operate remotely from different telescience centers located in the United States and Europe. The investigative Payload Integration Manager (iPIM) is the focal to assist organizations that have payloads operating in the MSG facility. NASA provides an MSG engineering unit for payload developers to verify that their hardware is operating properly before actual operation on the ISS. This paper will provide an overview of the MSG facility, a synopsis of the research that has already been accomplished in the MSG, and an overview of video and biological upgrades.

Scheduling Software for Complex Scenarios

NASA Technical Reports Server (NTRS)

2006-01-01

Preparing a vehicle and its payload for a single launch is a complex process that involves thousands of operations. Because the equipment and facilities required to carry out these operations are extremely expensive and limited in number, optimal assignment and efficient use are critically important. Overlapping missions that compete for the same resources, ground rules, safety requirements, and the unique needs of processing vehicles and payloads destined for space impose numerous constraints that, when combined, require advanced scheduling. Traditional scheduling systems use simple algorithms and criteria when selecting activities and assigning resources and times to each activity. Schedules generated by these simple decision rules are, however, frequently far from optimal. To resolve mission-critical scheduling issues and predict possible problem areas, NASA historically relied upon expert human schedulers who used their judgment and experience to determine where things should happen, whether they will happen on time, and whether the requested resources are truly necessary.

STS-107 crew poses for a group portrait during TCDT M113 training activities

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- -- The STS-107 crew poses for a group portrait with their instructor beside an M113 armored personnel carrier. The crew is participating in Terminal Countdown Demonstration Test activities, a standard part of launch preparations. In the front, from left, are Payload Specialist Ilan Ramon (the first Israeli astronaut), Instructor George Hoggard, Mission Specialist Laurel Clark, Commander Rick Husband, Mission Specialist David Brown, and Payload Commander Michael Anderson. In the back, from left, are Mission Specialist Kalpana Chawla and Pilot William 'Willie' McCool. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

Experiences in Delta mission planning

NASA Technical Reports Server (NTRS)

Kork, J.

1981-01-01

The Delta launch vehicle has experienced 153 successful launches since 1960 and 40 more are scheduled. Relying on up-to-date technology and proven flight hardware, the Delta vehicle has been used for low to high circular and geosynchronous transfer orbits, high elliptic probes, and lunar and planetary missions. A history of Delta launches and configuration modifications is presented, noting a 92-95% success rate and its cost effective role in reimbursable missions. Elements of mission planning such as feasibility studies (1-3 yrs), spacecraft restraints manuals, reference trajectories, preliminary mission analysis, detailed test objectives, range/safety studies, guided nominal trajectory, and mission specific studies are discussed. Trajectory shaping determines vehicle and spacecraft restraints, optimizes the trajectory, and maximizes the payload capabilities. Improvements in the Delta vehicle have boosted payloads from 100 to 2890 lbs., improving the price per pound ratio, as costs have risen, only by a factor of three. Current launch schedules extend well into 1985.

Structural design, analysis, and modal testing of the petite amateur navy satellite (PANSAT)

NASA Astrophysics Data System (ADS)

Sakoda, Daniel J.

1992-09-01

The Naval Postgraduate School's (NPS) Space Systems Academic Group is developing the Petite Amateur Navy Satellite (PANSAT), a small satellite for digital store-and-forward communication in the amateur frequency band. PANSAT is intended to be a payload of opportunity amendable to a number of launch vehicles. The Shuttle Small Self-Contained Payload (SSCP) program was chosen as a design baseline because of its high margins of safety as a manned system. The PANSAT structure design is presented for the launch requirements of a Shuttle SSCP. A finite element model was developed and studied for the design loads of a SSCP. The results showed the structure to be very robust and likely to accommodate the requirements of other launch vehicles. The finite element analysis was verified by model testing, correlating the fundamental mode of the finite element model with that of an engineering test structure.

Orion moved at Kennedy Space Center on This Week @NASA - October 3, 2014

NASA Image and Video Library

2014-10-03

On Sept. 28, NASA’s Orion spacecraft was moved from Kennedy Space Center’s Payload Hazardous Servicing Facility to its Launch Abort System Facility, for installation of its launch abort system, one of the many critical safety systems that will be evaluated during Orion’s un-crewed Exploration Flight Test -1, in December. NASA’s new deep space capsule is being developed to safely transport astronauts to and from Mars and other destinations on future missions. Also, Delta IV Heavy moved to the launch pad, U.S. spacewalks previewed, NASA and India to discuss joint exploration, Helicopter safety crash test, Combined Federal Campaign underway and Stop, Think, Connect!

PEGASO . Polar Explorer for Geomagnetic And other Scientific Observation

NASA Astrophysics Data System (ADS)

Romeo, G.; Di Stefano, G.; Di Felice, F.; Caprara, F.; Iarocci, A.; Peterzen, S.; Masi, S.; Spoto, D.; Ibba, R.; Musso, I.; Dragoy, P.

PEGASO (Polar Explorer for Geomagnetic And other Scientific Observation) program has been created to conduct small experiments in as many disciplines on-board of small stratospheric balloons. PEGASO uses the very low expensive pathfinder balloons. Stratospheric pathfinders are small balloons commonly used to explore the atmospheric circumpolar upper winds and to predict the trajectory for big LDBs (Long Duration Balloons). Installing scientific instruments on pathfinder and using solar energy to power supply the system, we have the opportunity to explorer the Polar Regions, during the polar summer, following circular trajectory. These stratospheric small payload have flown for 14 up to 40 days, measuring the magnetic field of polar region, by means of 3-axis-fluxgate magnetometer. PEGASO payload uses IRIDIUM satellite telemetry (TM). A ground station communicates with one or more payloads to download scientific and house-keeping data and to send commands for ballast releasing, for system resetting and for operating on the separator system at the flight end. The PEGASO missions have been performed from the Svalbard islands with the logistic collaboration of the Andoya Rocket Range and from the Antarctic Italian base. Continuous trajectory predictions, elaborated by Institute of Information Science and Technology (ISTI-CNR), were necessary for the flight safety requirements in the north hemisphere. This light payloads (<10 Kg) are realized by the cooperation between the INGV and the Physics department "La Sapienza" University and it has operated five times in polar areas with the sponsorship of Italian Antarctic Program (PNRA), Italian Space Agency (ASI). This paper summarizes important results about stratospheric missions.

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.

Autonomy and automation for Space Station housekeeping and maintenance functions

NASA Technical Reports Server (NTRS)

Turner, P. R.

1983-01-01

The Space Station crew will be a critical resource for economical operation of science and commercial payloads. Core station housekeeping and maintenance functions should be provided in a manner that requires a minimum of crew interaction. This paper outlines a prospective functional architecture for allocation of autonomous and automated control of these functions and discusses implementation issues arising from safety of manned operations, integration test requirements, and evolution of future station capabilities.

Fabrication and Testing of Ceramic Matrix Composite Propulsion Components

NASA Technical Reports Server (NTRS)

Effinger, Michael R.; Clinton, R. G., Jr.; Dennis, Jay; Elam, Sandy; Genge, Gary; Eckel, Andy; Jaskowiak, Martha H.; Kiser, J. Douglas; Lang, Jerry

2000-01-01

A viewgraph presentation outlines NASA's goals for the Second and Third Generation Reusable Launch Vehicles, placing emphasis on improving safety and decreasing the cost of transporting payloads to orbit. The use of ceramic matrix composite (CMC) technology is discussed. The development of CMC components, such as the Simplex CMC Blisk, cooled CMC nozzle ramps, cooled CMC thrust chambers, and CMC gas generators, are described, including challenges, test results, and likely future developments.

KSC-02pd1926

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, participates in Terminal Countdown Demonstration Test activities, a standard part of Shuttle launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

STS-99 crew talk to media after arrival at KSC for TCDT activities

NASA Technical Reports Server (NTRS)

2000-01-01

After their arrival at the Shuttle Landing Facility aboard T-38 training jet aircraft (background), the STS-99 crew talk to the media. From left are Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, and Gerhard Thiele, with the European Space Agency, Commander Kevin Kregel (at microphone) and Pilot Dominic Gorie. The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew talk to media after arrival at KSC for TCDT activities

NASA Technical Reports Server (NTRS)

2000-01-01

After their arrival at the Shuttle Landing Facility, the STS-99 crew talk to the media. At the microphone is Mission Specialist Gerhard Thiele, with the European Space Agency. At left is Commander Kevin Kregel. . The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Others taking part in the TCDT are Pilot Dominic Gorie and Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

KSC-00pp0007

NASA Image and Video Library

2000-01-11

After their arrival at the Shuttle Landing Facility, the STS-99 crew talk to the media. At the microphone is Mission Specialist Gerhard Thiele, with the European Space Agency. At left is Commander Kevin Kregel. . The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Others taking part in the TCDT are Pilot Dominic Gorie and Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0075

NASA Image and Video Library

2000-01-14

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Pilot Dominic Gorie, Mission Specialist Mamoru Mohri (Ph.D.), Mission Specialist Janice Voss (Ph.D.), Commander Kevin Kregel, Mission Specialist Janet Lynn Kavandi (Ph.D.), and Mission Specialist Gerhard Thiele (Ph.D.). Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0052

NASA Image and Video Library

2000-01-14

The STS-99 crew leave the Operations and Checkout Building on their way to Launch Pad 39A and a simulated countdown exercise. In the front row are Pilot Dominic Gorie and Commander Kevin Kregel; in the middle row are mission Specialists Janice Voss (Ph.D.) and Janet Lynn Kavandi (Ph.D.); in the back row are Mission Specialists Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, and Gerhard Thiele, who is with the European Space Agency. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0004

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, waves after his arrival at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic L. Pudwill Gorie, and Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), and Gerhard P.J. Thiele, with the European Space Agency. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0050

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level on the Fixed Service Structure, Launch Pad 39A, the STS-99 crew receive instructions about emergency egress. From left (in uniform) are Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Gerhard Thiele and Mamoru Mohri, Pilot Dominic Gorie and Commander Kevin Kregel. In the background can be seen the Vehicle Assembly Building at left and the waters of Banana Creek in between. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0051

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- In the bunker at Launch Pad 39A, the STS-99 crew try on oxygen masks. From left are Pilot Dominic Gorie, Mission Specialist Janice Voss (Ph.D.), Commander Kevin Kregel, and Mission Specialists Mamoru Mohri, Janet Lynn Kavandi (Ph.D.) and Gerhard Thiele. Mohri is with the National Space Development Agency (NASDA) of Japan and Thiele is with the European Space Agency. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0006

NASA Image and Video Library

2000-01-11

After their arrival at the Shuttle Landing Facility aboard T-38 training jet aircraft (background), the STS-99 crew talk to the media. From left are Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, and Gerhard Thiele, with the European Space Agency, Commander Kevin Kregel (at microphone) and Pilot Dominic Gorie. The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0075

NASA Image and Video Library

2000-01-14

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Pilot Dominic Gorie, Mission Specialist Mamoru Mohri (Ph.D.), Mission Specialist Janice Voss (Ph.D.), Commander Kevin Kregel, Mission Specialist Janet Lynn Kavandi (Ph.D.), and Mission Specialist Gerhard Thiele (Ph.D.). Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0004

NASA Image and Video Library

2000-01-11

STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, waves after his arrival at KSC aboard a T-38 training jet aircraft to take part in a Terminal Countdown Demonstration Test (TCDT). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Other crew members taking part are Commander Kevin Kregel, Pilot Dominic L. Pudwill Gorie, and Mission Specialists Janet Lynn Kavandi (Ph.D.), Janice Voss (Ph.D.), and Gerhard P.J. Thiele, with the European Space Agency. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0008

NASA Image and Video Library

2000-01-11

After their arrival at the Shuttle Landing Facility, the STS-99 crew talk to the media. At the microphone is Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan. The crew are here to take part in a Terminal Countdown Demonstration Test (TCDT), which provides simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. Others taking part in the TCDT are Commander Kevin Kregel, Pilot Dominic Gorie and Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), and Gerhard Thiele, with the European Space Agency. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

STS-99 crew try on oxygen masks during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

In the bunker at Launch Pad 39A, the STS-99 crew try on oxygen masks. From left are Pilot Dominic Gorie, Mission Specialist Janice Voss (Ph.D.), Commander Kevin Kregel, and Mission Specialists Mamoru Mohri, Janet Lynn Kavandi (Ph.D.) and Gerhard Thiele. Mohri is with the National Space Development Agency (NASDA) of Japan and Thiele is with the European Space Agency. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

Survey and evaluation of electrical power sources as to their potential application with the 500-pound Controlled Airdrop Cargo System. Final report

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

Dunlop, J.W.

1970-09-01

The 500-pound CACS is an electronically guided, gliding cargo airdrop system that can deliver critical materials and supplies to troops in remote or hostile areas at any time of day or night under a wide range of weather and terrain conditions. Because the drop aircraft does not have to fly directly over the target area, the aircrew conducting the drop is assured greater safety because the delivery aircraft can remain out of danger zones while making the drop. The CACS is currently in the Engineering Test phase. The system consists of a parawing glider, a control unit that receives signalsmore » from a transmitter and steers the glider, the payload, and the transmitter on which the glider homes. The system is capable of automatically delivering 300 to 600 pounds of cargo to within 200 feet of a ground radio transmitter from altitudes of 500 to 25,000 feet. The airborne portion, consisting of the parawing and the control unit, weighs approximately 80 pounds (excluding payload) and can be dropped from any cargo-carrying aircraft. The payload hits the ground with approximately the same impact as a parachute-dropped load, approximately 20 fps in vertical descent. Its horizontal velocity approaches 50 fps. (GRA)« less

KSC-00pp0053

NASA Image and Video Library

2000-01-14

In their orange flight suits, the STS-99 crew head toward the "astrovan" that will take them to Launch Pad 39A for a simulated countdown exercise. From left to right are Mission Specialists Mamoru Mohri (waving), Gerhard Thiele, Janice Voss (Ph.D.) and Janet Lynn Kavandi (Ph.D.), Pilot Dominic Gorie and Commander Kevin Kregel. Mohri is with the National Space Development Agency (NASDA) of Japan and Thiele is with the European Space Agency. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0050

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level on the Fixed Service Structure, Launch Pad 39A, the STS-99 crew receive instructions about emergency egress. From left (in uniform) are Mission Specialists Janice Voss (Ph.D.), Janet Lynn Kavandi (Ph.D.), Gerhard Thiele and Mamoru Mohri, Pilot Dominic Gorie and Commander Kevin Kregel. In the background can be seen the Vehicle Assembly Building at left and the waters of Banana Creek in between. The crew are taking part in Terminal Countdown Demonstration Test activities, which provide them with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, smiles during training on the M-113, an armored personnel carrier that is part of emergency egress training during Terminal Countdown Demonstration Test (TCDT) activities. The tracked vehicle could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Pilot Dominic Gorie , is ready to practice driving an armored personnel carrier that is part of emergency egress training and could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Behind him (left) is Mission Specialist Gerhard Thiele, who is with the European Space Agency. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities, STS-99 Mission Specialist Janice Voss (Ph.D.) is ready to practice driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M- 113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. In the rear (right) is Commander Kevin Kregel. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

Safety aspects of nuclear waste disposal in space

NASA Technical Reports Server (NTRS)

Rice, E. E.; Edgecombe, D. S.; Compton, P. R.

1981-01-01

Safety issues involved in the disposal of nuclear wastes in space as a complement to mined geologic repositories are examined as part of an assessment of the feasibility of nuclear waste disposal in space. General safety guidelines for space disposal developed in the areas of radiation exposure and shielding, containment, accident environments, criticality, post-accident recovery, monitoring systems and isolation are presented for a nuclear waste disposal in space mission employing conventional space technology such as the Space Shuttle. The current reference concept under consideration by NASA and DOE is then examined in detail, with attention given to the waste source and mix, the waste form, waste processing and payload fabrication, shipping casks and ground transport vehicles, launch site operations and facilities, Shuttle-derived launch vehicle, orbit transfer vehicle, orbital operations and space destination, and the system safety aspects of the concept are discussed for each component. It is pointed out that future work remains in the development of an improved basis for the safety guidelines and the determination of the possible benefits and costs of the space disposal option for nuclear wastes.

Casting ability of selected impression materials tested in different conditions in an in vitro sulcus model.

PubMed

Kolbeck, Carola; Rosentritt, Martin; Lang, Reinhold; Schiller, Manuela; Handel, Gerhard

2009-10-01

To test casting capacities of impression materials under dry and wet sulcular conditions in vitro. An incisor with a circular shoulder preparation (1 mm) was inserted in a primary mold. A shiftable secondary mold allowed adaptation of sulcular depth (1 to 4 mm). An outer circular chamfer assured reproducible positioning of an impression material carrier. Tested materials were PVS of differing viscosities (extra low, Panasil Contact Plus [ELV]; low, Affinis Light Body [LV]; and medium, Virtual Monophase [MV]) and one polyether material of low viscosity (Permadyne Garant [PE]). Impressions were made with sulcular depths of 1 to 4 mm in wet and 1 and 4 mm in dry conditions, cut in half, and digitized with a light microscope (Stemi SV8). Surface area of the region of interest (ROI, at inner angle of preparation) was determined with Optimas 6.2. Medians were calculated, and statistical analysis was performed using the Mann-Whitney U test (P # .05). Median values of the measurements under wet condition demonstrated the smallest ROI areas for the ELV (297-330[pixel]) and the MV (253-421[pixel]) materials followed by the LV (582-745[pixel]) and the PELV (544-823[pixel]). All materials showed significantly higher values for the wet compared to dry sulcular conditions. Repeated measurements showed no significant differences to the corresponding first determined series. The sulcus model is applicable to assess casting abilities of impression materials in clinically approximated sulcular conditions. The PVS materials with extra low and medium viscosities showed the best properties in dry and wet conditions.

Building on the Past - Looking to the Future. Part 2; A Focus on Expanding Horizons

NASA Technical Reports Server (NTRS)

Guidry, Richard W.; Nash, Sally K.; Rehm, Raymond B.; Wolf, Scott L.; Wong, Teresa K.

2010-01-01

The history of space endeavors stretches far from Robert Goddard s initial flights and will certainly extend far beyond the construction of the International Space Station. As society grows in knowledge of and familiarity with space, the focus of maintaining the safety of the crews and the habitability of the vehicles will be of the utmost importance to the National Aeronautics and Space Administration (NASA) community. Through the years, Payload Safety has developed not only as a Panel, but also as part of the NASA community, striving to enhance the efficiency and understanding of how business should be conducted as more International Partners become involved. The recent accomplishments of the first docking of the Japan Aerospace Exploration Agency (JAXA) HII Transfer Vehicle (HTV 1) and completion of the Japanese Experiment Module (JEM) or KIBO and the Russian MRM2 to the International Space Station (ISS) mark significant steps for the future of ISS. 2010 will mark the final flights of the Shuttle and the completion of ISS assembly. Future delivery of humans and hardware will rely on the Russian Progress and Soyuz, the Japanese HII Transfer Vehicle (HTV), the European Automated Transfer Vehicle (ATV) and US "Commercial Off-The-Shelf" (COTS) and Constellation vehicles. The International Partners (IPs) will have more capability in delivery as well as responsibility for review of hardware they deliver to assure safe operation. This is the second in a series of papers and presentations in what is hoped to be an annual update that illustrates challenges and lessons learned in the areas of communication (how hazard reports can be misunderstood), safety requirements (transitioning from Shuttle-centric to ISS-centric), and processes (review of hardware by RSC-E and Franchised ESA and JAXA PSRP) which have been vital in conducting the business of the Payload Safety Review Panel (PSRP). This year will focus on the items annotated above.

Requirements for significant problem reporting and trend analysis

NASA Technical Reports Server (NTRS)

1988-01-01

This handbook supplements policies, requirements, and procedures of NMI 8070.3 to ensure that NASA management at each organizational level is: fully aware of trends affecting both the level of safety and the potential for mission success established for both NASA manned space programs and its supporting institutions; fully and independently informed of problems that represent significant risk to the safety of all personnel (including the general populace) and to the success of a mission or operation through a program mechanism herein defined as Significant Problem Reporting; and in full agreement with the level of elimination of these problems through the closed-loop accounting of corrective actions. The requirements of this handbook are supportive of the agency's safety, reliability, maintainability, and quality assurance (SRM&QA) program objectives and are applicable to all organizational elements of NASA connected with or supporting developmental or operational manned space program/projects (including associated payloads) and the related institutional facilities.

Structural verification for GAS experiments

NASA Technical Reports Server (NTRS)

Peden, Mark Daniel

1992-01-01

The purpose of this paper is to assist the Get Away Special (GAS) experimenter in conducting a thorough structural verification of its experiment structural configuration, thus expediting the structural review/approval process and the safety process in general. Material selection for structural subsystems will be covered with an emphasis on fasteners (GSFC fastener integrity requirements) and primary support structures (Stress Corrosion Cracking requirements and National Space Transportation System (NSTS) requirements). Different approaches to structural verifications (tests and analyses) will be outlined especially those stemming from lessons learned on load and fundamental frequency verification. In addition, fracture control will be covered for those payloads that utilize a door assembly or modify the containment provided by the standard GAS Experiment Mounting Plate (EMP). Structural hazard assessment and the preparation of structural hazard reports will be reviewed to form a summation of structural safety issues for inclusion in the safety data package.

Tanker Argus: Re-supply for a LEO Cryogenic Propellant Depot

NASA Astrophysics Data System (ADS)

St. Germain, B.; Olds, J.; Kokan, T.; Marcus, L.; Miller, J.

The Argus reusable launch vehicle (RLV) concept is a single-stage-to-orbit conical, winged bodied vehicle powered by two liquid hydrogen/liquid oxygen supercharged ejector ramjets. The 3rd generation Argus launch vehicle utilizes advanced vehicle technologies along with a Maglev launch assist track. A tanker version of the Argus RLV is envisioned to provide an economical means of providing liquid fuel and oxidizer to an orbiting low-Earth orbit (LEO) propellant depot. This depot could then provide propellant to various spacecraft, including reusable orbital transfer vehicles used to ferry space solar power satellites to geo-stationary orbit. Two different tanker Argus configurations were analyzed. The first simply places additional propellant tanks inside the payload bay of an existing Argus reusable launch vehicle. The second concept is a modified Argus RLV in which the payload bay is removed and the vehicle propellant tanks are stretched to hold extra propellant. An iterative conceptual design process was used to design both Argus vehicles. This process involves various disciplines including aerodynamics, trajectory analysis, weights &structures, propulsion, operations, safety, and cost/economics. The payload bay version of tanker Argus, which has a gross mass of 256.3MT, is designed to deliver a 9.07MT payload to LEO. This payload includes propellant and the tank structure required to secure this propellant in the payload bay. The modified, pure tanker version of Argus has a gross mass of 218.6MT and is sized to deliver a full 9.07MT of propellant to LEO. The economic analysis performed for this study involved the calculation of many factors including the design/development and recurring costs of each vehicle. These results were used along with other economic assumptions to determine the "per kilogram" cost of delivering propellant to orbit. The results show that for a given flight rate the "per kilogram" cost is cheaper for the pure tanker version of Argus. However, the main goal of this study was to determine at which flight rate would it be financially beneficial to spend more development money to modify an existing, sunk cost, payload bay version of Argus in order to create a more efficient pure tanker version. For flight rates greater than approximately 320 flights/year, there is only a small financial motivation to develop a pure tanker version. At this flight rate both versions of Argus are able to deliver propellant to LEO at an approximate cost of 375/kg.

Safety divers prepare HST mockup in the Neutral Buoyancy Simulator at MSFC

NASA Image and Video Library

1993-06-01

Safety divers in the Neutral Buoyancy Simulator (NBS) at the Marshall Space Flight Center (MSFC) prepare a mockup of the Hubble Space Telescope (HST) for one of 32 separate training sessions conducted by four of the STS-61 crew members in June. The three-week process allowed mission trainers to refine the timelines for the five separate spacewalks scheduled to be conducted on the actual mission scheduled for December 1993. The HST is separated into two pieces since the water tank depth cannot support the entire structure in one piece. The full length payload bay mockup shows the Solar Array Carrier in the foreground and the various containers that will house replacement hardware that will be carried on the mission.

Tough Textiles Protect Payloads and Public Safety Officers

NASA Technical Reports Server (NTRS)

2009-01-01

In order to create the Mars Pathfinder s mission-critical airbags in the 1990s, NASA s Jet Propulsion Laboratory collaborated with New Ipswich, New Hampshire s Warwick Mills Inc. to weave multi-layer textiles for the airbags for both Pathfinder and the Mars Exploration Rovers. Warwick Mills applied techniques from the collaboration to its puncture- and impact-resistant TurtleSkin product line. The company's metal flex armor (MFA) vests offer stab protection comparable with rigid steel plates and over 50,000 of the vests have sold. The SoftPlate body armor offers protection from handgun bullets, and like the MFA, is designed to be more comfortable than rigid vests. International public safety and military customers are now benefiting from the TurtleSkin products.

System safety checklist Skylab program report

NASA Technical Reports Server (NTRS)

Mcnail, E. M.

1974-01-01

Design criteria statement applicable to a wide variety of flight systems, experiments and other payloads, associated ground support equipment and facility support systems are presented. The document reflects a composite of experience gained throughout the aerospace industry prior to Skylab and additional experience gained during the Skylab Program. It has been prepared to provide current and future program organizations with a broad source of safety-related design criteria and to suggest methods for systematic and progressive application of the criteria beginning with preliminary development of design requirements and specifications. Recognizing the users obligation to shape the checklist to his particular needs, a summary of the historical background, rationale, objectives, development and implementation approach, and benefits based on Skylab experience has been included.

Fighting the Russians in Winter: Three Case Studies (Leavenworth Papers, Number 5)

DTIC Science & Technology

1981-12-01

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A system dynamics approach to develop a recovery model in the Malaysian automotive industry

NASA Astrophysics Data System (ADS)

Mohamad-Ali, N.; Ghazilla, R. A. R.; Abdul-Rashid, S. H.; Sakundarini, N.; Ahmad-Yazid, A.; Stephenie, L.

2017-06-01

Design strategies play a significant role to enhance recovery effectiveness at the end of product life cycle. By reviewing previous study, there are many factors involved to enhance recovery effectiveness but limited to linking design strategies factors in holistic and dynamics view. Proposed method are explained and an initial model for end-of-life vehicles (ELVs) recovery model illustrated in graphical and numerical data is presented. However this is limited to authors understanding and preliminary data which requires collaboration between designers and other stakeholders to develop a model based on actual situation.

Analytical Assessment of the Reciprocating Feed System

NASA Technical Reports Server (NTRS)

Eddleman, David E.; Blackmon, James B.; Morton, Christopher D.

2006-01-01

A preliminary analysis tool has been created in Microsoft Excel to determine deliverable payload mass, total system mass, and performance of spacecraft systems using various types of propellant feed systems. These mass estimates are conducted by inserting into the user interface the basic mission parameters (e.g., thrust, burn time, specific impulse, mixture ratio, etc.), system architecture (e.g., propulsion system type and characteristics, propellants, pressurization system type, etc.), and design properties (e.g., material properties, safety factors, etc.). Different propellant feed and pressurization systems are available for comparison in the program. This gives the user the ability to compare conventional pressure fed, reciprocating feed system (RFS), autogenous pressurization thrust augmentation (APTA RFS), and turbopump systems with the deliverable payload, inert mass, and total system mass being the primary comparison metrics. Analyses of several types of missions and spacecraft were conducted and it was found that the RFS offers a performance improvement, especially in terms of delivered payload, over conventional pressure fed systems. Furthermore, it is competitive with a turbopump system at low to moderate chamber pressures, up to approximately 1,500 psi. Various example cases estimating the system mass and deliverable payload of several types of spacecraft are presented that illustrate the potential system performance advantages of the RFS. In addition, a reliability assessment of the RFS was conducted, comparing it to simplified conventional pressure fed and turbopump systems, based on MIL-STD 756B; these results showed that the RFS offers higher reliability, and thus substantially longer periods between system refurbishment, than turbopump systems, and is competitive with conventional pressure fed systems. This is primarily the result of the intrinsic RFS fail-operational capability with three run tanks, since the system can operate with just two run tanks.

A Year of Progress: NASA's Space Launch System Approaches Critical Design Review

NASA Technical Reports Server (NTRS)

Askins, Bruce; Robinson, Kimberly

2015-01-01

NASA's Space Launch System (SLS) made significant progress on the manufacturing floor and on the test stand in 2014 and positioned itself for a successful Critical Design Review in mid-2015. SLS, the world's only exploration-class heavy lift rocket, has the capability to dramatically increase the mass and volume of human and robotic exploration. Additionally, it will decrease overall mission risk, increase safety, and simplify ground and mission operations - all significant considerations for crewed missions and unique high-value national payloads. Development now is focused on configuration with 70 metric tons (t) of payload to low Earth orbit (LEO), more than double the payload of the retired Space Shuttle program or current operational vehicles. This "Block 1" design will launch NASA's Orion Multi-Purpose Crew Vehicle (MPCV) on an uncrewed flight beyond the Moon and back and the first crewed flight around the Moon. The current design has a direct evolutionary path to a vehicle with a 130t lift capability that offers even more flexibility to reduce planetary trip times, simplify payload design cycles, and provide new capabilities such as planetary sample returns. Every major element of SLS has successfully completed its Critical Design Review and now has hardware in production or testing. In fact, the SLS MPCV-to-Stage-Adapter (MSA) flew successfully on the Exploration Flight Test (EFT) 1 launch of a Delta IV and Orion spacecraft in December 2014. The SLS Program is currently working toward vehicle Critical Design Review in mid-2015. This paper will discuss these and other technical and programmatic successes and challenges over the past year and provide a preview of work ahead before the first flight of this new capability.

Glovebox and Experiment Safety

NASA Astrophysics Data System (ADS)

Maas, Gerard

2005-12-01

Human spaceflight hardware and operations must comply with NSTS 1700.7. This paper discusses how a glovebox can help.A short layout is given on the process according NSTS/ISS 13830, explaining the responsibility of the payload organization, the approval authority of the PSRP and the defined review phases (0 till III).Amongst others, the following requirement has to be met:"200.1 Design to Tolerate Failures. Failure tolerance is the basic safety requirement that shall be used to control most payload hazards. The payload must tolerate a minimum number of credible failures and/or operator errors determined by the hazard level. This criterion applies when the loss of a function or the inadvertent occurrence of a function results in a hazardous event.200.1a Critical Hazards. Critical hazards shall be controlled such that no single failure or operator error can result in damage to STS/ISS equipment, a nondisabling personnel injury, or the use of unscheduled safing procedures that affect operations of the Orbiter/ISS or another payload.200.1b Catastrophic Hazards. Catastrophic hazards shall be controlled such that no combination of two failures or operator errors can result in the potential for a disabling or fatal personnel injury or loss of the Orbiter/ISS, ground facilities or STS/ISS equipment."For experiments in material science, biological science and life science that require real time operator manipulation, the above requirement may be hard or impossible to meet. Especially if the experiment contains substances that are considered hazardous when released into the habitable environment. In this case operation of the experiment in a glovebox can help to comply.A glovebox provides containment of the experiment and at the same time allows manipulation and visibility to the experiment.The containment inside the glovebox provides failure tolerance because the glovebox uses a negative pressure inside the working volume (WV). The level of failure tolerance is dependent of: the identified failure case and the hazardous substance being released (chemical, biological or different).The principle of the glovebox operation is explained, including: mechanical enclosure, air circulation, air filtration and operational modes.Limitations of the glovebox are presented: inability of an experiment fire to be detected by the ASDA, containment only with respect to specified substances, etc. There are requirements induced by the glovebox that the experiment must comply with: Compatibility with the glovebox filter system, thermal limitations, safe without glovebox services, parameter monitoring when a fire hazard is credible, sufficient containment when entering the glovebox and after the experiment, etc.Experiments that are using a glovebox to be operated in shall assess this integrated set-up and the associated operations for compliance to the safety requirements. During this assessment the PSRP shall determine if the provided failure tolerance is sufficient.The gloveboxes that Bradford Engineering (co-) built for human space flight are: USML-1 and 2, MGBX (STS and MIR), MSG, PGBX, LSG-WVA, BGB and PGB. Some of the evolutions are pointed out (experiment services added without compromising safety levels). The major differences of the gloveboxes are presented. For the gloveboxes that are in operation at this time (MSG) or in the near future (BGB, LSG- WVA and PGB) the specific applications are presented.

Overview of the Microgravity Science Glovebox (MSG) Facility and the Research Performed in the MSG

NASA Technical Reports Server (NTRS)

Jordan, Lee

2016-01-01

The Microgravity Science Glovebox (MSG) is a rack facility aboard the International Space Station (ISS) designed for investigation handling. The MSG was built by the European Space Agency (ESA) which also provides sustaining engineering support for the facility. The MSG has been operating on the ISS since July 2002 and is currently located in the US Laboratory Module. The unique design of the facility allows it to accommodate science and technology investigations in a "workbench" type environment. The facility has an enclosed working volume that is held at a negative pressure with respect to the crew living area. This allows the facility to provide two levels of containment for small parts, particulates, fluids, and gases. This containment approach protects the crew from possible hazardous operations that take place inside the MSG work volume. Research investigations operating inside the MSG are provided a large 255 liter enclosed work space, 1000 watts of direct current power via a versatile supply interface (120, 28, plus or minus 12, and 5 volts direct current), 1000 watts of cooling capability, video and data recording and real time downlink, ground commanding capabilities, access to ISS Vacuum Exhaust and Vacuum Resource Systems, and gaseous nitrogen supply. These capabilities make the MSG one of the most utilized facilities on ISS. The MSG has been used for over 27,000 hours of scientific payload operations. MSG investigations involve research in cryogenic fluid management, fluid physics, spacecraft fire safety, materials science, combustion, plant growth, biological studies and life support technology. The MSG facility is operated by the Payloads Operations Integration Center at Marshall Space Flight Center. Payloads may also operate remotely from different telescience centers located in the United States and Europe. The Investigative Payload Integration Manager (IPIM) is the focal to assist organizations that have payloads operating in the MSG facility. NASA provides an MSG engineering unit for payload developers to verify that their hardware is operating properly before actual operation on the ISS. This poster will provide an overview of the MSG facility, a synopsis of the research that has already been accomplished in the MSG, and an overview of video and biological upgrades. The author would like to acknowledge Teledyne Brown Engineering and the entire MSG Team for their inputs into this poster.

LERC power system autonomy program 1990 demonstration

NASA Technical Reports Server (NTRS)

Faymon, Karl A.; Sundberg, Gale R.; Bercaw, Robert R.; Weeks, David J.

1987-01-01

The NASA Lewis Research Center has undertaken a program for the development of space systems automation, with a view to increased reliability, safety, payload capability, and decreased operational costs. The NASA Space Station is a primary area of application for the techniques thus developed. Attention is presently given to the activities associated with the Power Systems Autonomy Demonstration Project, which has a projected demonstration date in 1990 and will integrate knowledge-based systems into a real-time environment. Two coordinated systems under expert system control will be demonstrated.

New NRO Eastern Processing Facility at Cape Canaveral Air Force Station Florida. Environmental Assessment:

DTIC Science & Technology

2005-08-31

to the launch complex is considered a hazardous operation. Transportation of fueled payloads will comply with AFSPCMAN 91 - 710 , Range Safety User...April. 45th Space Wing (SW). 1996b. Hazardous Materials Response Plan 32- 3 , Volume I, March. 45th Space Wing (SW). 2001. Integrated Natural...control number. 1. REPORT DATE 31 AUG 2005 2. REPORT TYPE 3 . DATES COVERED 00-00-2005 to 00-00-2005 4. TITLE AND SUBTITLE Final Environmental

Computer-Aided Design (CAD) Tools to Support the Human Factors Design Teams

NASA Technical Reports Server (NTRS)

Null, Cynthia H.; Jackson, Mariea D.; Perry, Trey; Quick, Jason C.; Stokes, Jack W.

2014-01-01

The scope of this assessment was to develop a library of basic 1-Gravity (G) human posture and motion elements used to construct complex virtual simulations of ground processing and maintenance tasks for spaceflight vehicles, including launch vehicles, crewed spacecraft, robotic spacecraft, satellites, and other payloads. The report herein describes the task, its purpose, performance, findings, NASA Engineering and Safety Center (NESC) recommendations, and conclusions in the definition and assemblage of the postures and motions database (PMD).

Control System Upgrade for a Mass Property Measurement Facility

NASA Technical Reports Server (NTRS)

Chambers, William; Hinkle, R. Kenneth (Technical Monitor)

2002-01-01

The Mass Property Measurement Facility (MPMF) at the Goddard Space Flight Center has undergone modifications to ensure the safety of Flight Payloads and the measurement facility. The MPMF has been technically updated to improve reliability and increase the accuracy of the measurements. Modifications include the replacement of outdated electronics with a computer based software control system, the addition of a secondary gas supply in case of a catastrophic failure to the gas supply and a motor controlled emergency stopping feature instead of a hard stop.

Lightsats and their attraction to budget oriented Federal agencies

NASA Technical Reports Server (NTRS)

Bonsall, Charles A.

1988-01-01

The term Lightsats refers to low volume, low mass, low Earth orbit, satellites suitable for launch from Get Away Special canisters, or as secondary payloads on expendable launch vehicles. New or existing technology that offers potential to improve the safety, capacity and efficiency of the National Airspace System is discussed. The discussion is presented from the point of view of an individual within a government agency who wants to see a new technology to enhance the mission of that agency.

KSC-02pd1934

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- -- STS-107 Payload Commander Michael Anderson takes a break during training on the operation of an M113 armored personnel carrier during Terminal Countdown Demonstration Test activities, a standard part of launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

KSC-02pd1931

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, the first Israeli astronaut, takes a break during training on the operation of an M113 armored personnel carrier during Terminal Countdown Demonstration Test activities, a standard part of launch preparations. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. Launch is planned for Jan. 16, 2003, between 10 a.m. and 2 p.m. EST aboard Space Shuttle Columbia.

Status of advanced orbital transfer propulsion

NASA Technical Reports Server (NTRS)

Cooper, L. P.

1985-01-01

A new Orbital Transfer Vehicle (OTV) propulsion system that will be used in conjunction with the Space Shuttle, Space Station and Orbit Maneuvering Vehicle is discussed. The OTV will transfer men, large space structures and conventional payloads between low Earth and higher energy orbits. Space probes carried by the OTV will continue the exploration of the solar system. When lunar bases are established, the OTV will be their transportation link to Earth. Critical engine design considerations based upon the need for low cost payload delivery, space basing, reusability, aeroassist maneuvering, low g transfers of large space structures and man rating are described. The importance of each of these to propulsion design is addressed. Specific propulsion requirements discussed are: (1) high performance H2/O2 engine; (2) multiple engine configurations totalling no more than 15,000 lbf thrust 15 to 20 hr life; (3) space maintainable modular design; (4) health monitoring capability; and (5) safety and mission success with backup auxiliary propulsion.

KSC-04pd1672

NASA Image and Video Library

2004-08-23

KENNEDY SPACE CENTER, FLA. - The Remote Manipulator System (RMS), also known as the Canadian robotic arm, for the orbiter Discovery has arrived at KSC’s Vehicle Assembly Building Lab. Seen on the left end is the shoulder pitch joint. The wrist and shoulder joints on the RMS allow the basic structure of the arm to maneuver similar to a human arm. The RMS is used to deploy and retrieve payloads, provide a mobile extension ladder or foot restraints for crew members during extravehicular activities; and to aid the flight crew members in viewing surfaces of the orbiter or payloads through a television camera on the RMS. The arm is also serving as the base for the new Orbiter Boom Sensor System (OBSS), one of the safety measures for Return to Flight, equipping the Shuttle with cameras and laser systems to inspect the Shuttle’s Thermal Protection System while in space. Discovery is scheduled for a launch planning window of March 2005 on mission STS-114.

Preliminary analysis of space mission applications for electromagnetic launchers

NASA Technical Reports Server (NTRS)

Miller, L. A.; Rice, E. E.; Earhart, R. W.; Conlon, R. J.

1984-01-01

The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed. Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of launching to space payloads of 800 KG or more. A hybrid launcher in which EML is used for the first 2 KM/sec followed by chemical rocket stages was also tested. A cost estimates study shows that one to two EML launches per day are needed to break even, compared to a four-stage rocket. Development models are discussed for: (1) Earth orbital missions; (2) lunar base supply mission; (3) solar system escape mission; (4) Earth escape missions; (5) suborbital missions; (6) electromagnetic boost missions; and (7) space-based missions. Safety factors, environmental impacts, and EML systems analysis are discussed. Alternate systems examined include electrothermal thrustors, an EML rocket gun; an EML theta gun, and Soviet electromagnetic accelerators.

On-Board Software Reference Architecture for Payloads

NASA Astrophysics Data System (ADS)

Bos, Victor; Rugina, Ana; Trcka, Adam

2016-08-01

The goal of the On-board Software Reference Architecture for Payloads (OSRA-P) is to identify an architecture for payload software to harmonize the payload domain, to enable more reuse of common/generic payload software across different payloads and missions and to ease the integration of the payloads with the platform.To investigate the payload domain, recent and current payload instruments of European space missions have been analyzed. This led to a Payload Catalogue describing 12 payload instruments as well as a Capability Matrix listing specific characteristics of each payload. In addition, a functional decomposition of payload software was prepared which contains functionalities typically found in payload systems. The definition of OSRA-P was evaluated by case studies and a dedicated OSRA-P workshop to gather feedback from the payload community.

Robotics

NASA Technical Reports Server (NTRS)

Ambrose, Robert O.

2007-01-01

Lunar robotic functions include: 1. Transport of crew and payloads on the surface of the moon; 2. Offloading payloads from a lunar lander; 3. Handling the deployment of surface systems; with 4. Human commanding of these functions from inside a lunar vehicle, habitat, or extravehicular (space walk), with Earth-based supervision. The systems that will perform these functions may not look like robots from science fiction. In fact, robotic functions may be automated trucks, cranes and winches. Use of this equipment prior to the crew s arrival or in the potentially long periods without crews on the surface, will require that these systems be computer controlled machines. The public release of NASA's Exploration plans at the 2nd Space Exploration Conference (Houston, December 2006) included a lunar outpost with as many as four unique mobility chassis designs. The sequence of lander offloading tasks involved as many as ten payloads, each with a unique set of geometry, mass and interface requirements. This plan was refined during a second phase study concluded in August 2007. Among the many improvements to the exploration plan were a reduction in the number of unique mobility chassis designs and a reduction in unique payload specifications. As the lunar surface system payloads have matured, so have the mobility and offloading functional requirements. While the architecture work continues, the community can expect to see functional requirements in the areas of surface mobility, surface handling, and human-systems interaction as follows: Surface Mobility 1. Transport crew on the lunar surface, accelerating construction tasks, expanding the crew s sphere of influence for scientific exploration, and providing a rapid return to an ascent module in an emergency. The crew transport can be with an un-pressurized rover, a small pressurized rover, or a larger mobile habitat. 2. Transport Extra-Vehicular Activity (EVA) equipment and construction payloads. 3. Transport habitats and power modules over long distances, pre-positioning them for the arrival of crew on a subsequent lander. Surface Handling 1. Offload surface system payloads from the lander, breaking launch restraints and power/data connections. Payloads may be offloaded to a wheeled vehicle for transport. 2. Deploy payloads from a wheeled vehicle at a field site, placing the payloads in their final use site on the ground or mating them with existing surface systems. 3. Support regolith collection, site preparation, berm construction, or other civil engineering tasks using tools and implements attached to rovers. Human-Systems Interaction 1. Provide a safe command and control interface for suited EVA to ride on and drive the vehicles, making sure that the systems are also safe for working near dismounted crew. 2. Provide an effective control system for IV crew to tele-operate vehicles, cranes and other equipment from inside the surface habitats with evolving independence from Earth. .. Provide a supervisory system that allows machines to be commanded from the ground, working across the Earth-Lunar time delays on the order of 5-10 seconds (round trip) to support operations when crew are not resident on the surface. Technology Development Needs 1. Surface vehicles that can dock, align and mate with outpost equipment such as landers, habitats and fluid/power interfaces. 2. Long life motors, drive trains, seals, motor electronics, sensors, processors, cable harnesses, and dash board displays. 3. Active suspension control, localization, high speed obstacle avoidance, and safety systems for operating near dismounted crew. 4. High specific energy and specific power batteries that are safe, rechargeable, and long lived.

KSC00pp0074

NASA Image and Video Library

2000-01-14

KENNEDY SPACE CENTER, Fla. -- At Launch Pad 39A, STS-99 Mission Specialists Gerhard Thiele (Ph.D.), of the European Space Agency (in front), and Janet Kavandi (Ph.D.) prepare to practice emergency egress procedures with a slidewire basket. Seven slidewires, with flatbottom baskets suspended from each wire, extend from the Fixed Service Structure at the orbiter access arm level. These baskets could provide an escape route for the astronauts until the final 30 seconds of the countdown in case of an emergency. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

KSC-00pp0016

NASA Image and Video Library

2000-01-12

STS-99 Pilot Dominic Gorie, under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Riding in the rear are Mission Specialists Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, Janet Lynn Kavandi (Ph.D.) and Janice Voss (Ph.D.). TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0016

NASA Image and Video Library

2000-01-12

STS-99 Pilot Dominic Gorie, under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Riding in the rear are Mission Specialists Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, Janet Lynn Kavandi (Ph.D.) and Janice Voss (Ph.D.). TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0074

NASA Image and Video Library

2000-01-14

KENNEDY SPACE CENTER, Fla. -- At Launch Pad 39A, STS-99 Mission Specialists Gerhard Thiele (Ph.D.), of the European Space Agency (in front), and Janet Kavandi (Ph.D.) prepare to practice emergency egress procedures with a slidewire basket. Seven slidewires, with flatbottom baskets suspended from each wire, extend from the Fixed Service Structure at the orbiter access arm level. These baskets could provide an escape route for the astronauts until the final 30 seconds of the countdown in case of an emergency. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

KSC00pp0044

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 167-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Mission Specialist Janet Lynn Kavandi (Ph.D.), Commander Kevin Kregel, Mission Specialists Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. Behind them (left) are visible the top of a solid rocket booster (white) and external tank (orange). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0044

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 167-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Mission Specialist Janet Lynn Kavandi (Ph.D.), Commander Kevin Kregel, Mission Specialists Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. Behind them (left) are visible the top of a solid rocket booster (white) and external tank (orange). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC-00pp0043

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 167-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Mission Specialist Janet Lynn Kavandi (Ph.D.), Commander Kevin Kregel, Mission Specialists Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. Behind them are visible the top of a solid rocket booster (white) and external tank (orange). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

KSC00pp0043

NASA Image and Video Library

2000-01-13

KENNEDY SPACE CENTER, Fla. -- At the 167-foot level of the Fixed Service Structure on Launch Pad 39A, the STS-99 crew pose for a photograph during Terminal Countdown Demonstration Test (TCDT) activities. Standing left to right are Mission Specialist Janet Lynn Kavandi (Ph.D.), Commander Kevin Kregel, Mission Specialists Janice Voss (Ph.D.), Gerhard Thiele and Mamoru Mohri, and Pilot Dominic Gorie. Thiele is with the European Space Agency and Mohri is with the National Space Development Agency (NASDA) of Japan. Behind them are visible the top of a solid rocket booster (white) and external tank (orange). The TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST

STS-99 crew check out emergency egress equipment at launch pad during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

At Launch Pad 39A, STS-99 Mission Specialists Gerhard Thiele (Ph.D.), of the European Space Agency (in front), and Janet Kavandi (Ph.D.) prepare to practice emergency egress procedures with a slidewire basket. Seven slidewires, with flatbottom baskets suspended from each wire, extend from the Fixed Service Structure at the orbiter access arm level. These baskets could provide an escape route for the astronauts until the final 30 seconds of the countdown in case of an emergency. The crew is taking part in Terminal Countdown Demonstration Test (TCDT) activities that provide the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

A path to in-space welding and to other in-space metal processing technologies using Space Shuttle small payloads

NASA Technical Reports Server (NTRS)

Tamir, David

1992-01-01

As we venture into space, it becomes necessary to assemble, expand, and repair space-based structures for our housing, research, and manufacturing. The zero gravity-vacuum of space challenges us to employ construction options which are commonplace on Earth. Rockwell International (RI) has begun to undertake the challenge of space-based construction via numerous options, of which one is welding. As of today, RI divisions have developed appropriate resources and technologies to bring space-based welding within our grasp. Further work, specifically in the area of developing space experiments to test RI technology, is required. RI Space Welding Project's achievements to date, from research and development (R&E) efforts in the areas of microgravity, vacuum, intra- / extra- vehicular activity and spinoff technologies, are reviewed. Special emphasis is given to results for G-169's (Get Away Special) microgravity flights aboard a NASA KC-135. Based on these achievements, a path to actual development of a space welding system is proposed with options to explore spinoff in-space metal processing technologies. This path is constructed by following a series of milestone experiments, of which several are to utilize NASA's Shuttle Small Payload Programs. Conceptual designs of the proposed shuttle payload experiments are discussed with application of lessons learned from G-169's design, development, integration, testing, safety approval process, and KC-135 flights.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

STS-99 Pilot Dominic Gorie, under the watchful eye of Capt. George Hoggard, a trainer with the KSC Fire Department, practices driving the M-113, an armored personnel carrier. Part of Terminal Countdown Demonstration Test (TCDT) activities, the M-113 could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Riding in the rear are Mission Specialists Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, Janet Lynn Kavandi (Ph.D.) and Janice Voss (Ph.D.). TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station-derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

The Space Shuttle orbiter payload retention systems

NASA Technical Reports Server (NTRS)

Hardee, J. H.

1982-01-01

Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.

Shaping NASA's Kennedy Space Center Safety for the Future

NASA Technical Reports Server (NTRS)

Kirkpatrick, Paul; McDaniel, Laura; Smith, Maynette

2011-01-01

With the completion of the Space Shuttle Program, the Kennedy Space Center (KSC) safety function will be required to evolve beyond the single launch vehicle launch site focus that has held prominence for almost fifty years. This paper will discuss how that evolution is taking place. Specifically, we will discuss the future of safety as it relates to a site that will have multiple, very disparate, functions. These functions will include new business; KSC facilities not under the control of NASA; traditional payload and launch vehicle processing; and, operations conducted by NASA personnel, NASA contractors or a combination of both. A key element in this process is the adaptation of the current KSC set of safety requirements into a multi-faceted set that can address each of the functions above, while maintaining our world class safety environment. One of the biggest challenges that will be addressed is how to protect our personnel and property without dictating how other Non-NASA organizations protect their own employees and property. The past history of KSC Safety will be described and how the lessons learned from previous programs will be applied to the future. The lessons learned from this process will also be discussed as information for other locations that may undergo such a transformation.

Test and model correlation of the atmospheric emission photometric imager fiberglass pedestal

NASA Technical Reports Server (NTRS)

Lee, H. M., III; Barker, L. A.

1990-01-01

The correlation is presented of the static loads testing and finite element modeling for the fiberglass pedestal used on the Atmospheric Emission Photometric Imaging (AEPI) experiment. This payload is to be launched in the space shuttle as part of the ATLAS-1 experiment. Strain gauge data from rosettes around the highly loaded base are compared to the same load case run for the Spacelab 1 testing done in 1981. Correlation of the model and test data was accomplished through comparison of the composite stress invariant using the expected flight loads for the ATLAS-1 mission. Where appropriate, the Tsai-Wu failure criteria was used in the development of the key margins of safety. Margins of safety are all positive for the pedestal and are reported.

Space Station accommodation of attached payloads

NASA Technical Reports Server (NTRS)

Browning, Ronald K.; Gervin, Janette C.

1987-01-01

The Attached Payload Accommodation Equipment (APAE), which provides the structure to attach payloads to the Space Station truss assembly, to access Space Station resources, and to orient payloads relative to specified targets, is described. The main subelements of the APAE include a station interface adapter, payload interface adapter, subsystem support module, contamination monitoring system, payload pointing system, and attitude determination system. These components can be combined to provide accommodations for small single payloads, small multiple payloads, large self-supported payloads, carrier-mounted payloads, and articulated payloads. The discussion also covers the power, thermal, and data/communications subsystems and operations.

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.

Safety Assessment of Multi Purpose Small Payload Rack(MSPR)

NASA Astrophysics Data System (ADS)

Mizutani, Yoshinobu; Takada, Satomi; Murata, Kosei; Ozawa, Daisaku; Kobayashi, Ryoji; Nakamura, Yasuhiro

2010-09-01

We are reporting summary of preliminary safety assessment for Multi Purpose Small Payload Rack(MSPR), which is one of the micro gravity experiment facilities that are being developed for the 2nd phase JEM utilization(JEM: Japanese Experiment Module) that will be launched on H-II Transfer Vehicle(HTV) 2nd flight in 2011. MSPR is used for multi-purpose micro-g experiment providing experimental spaces and work stations. MSPR has three experimental spaces; first, there is a space called Work Volume(WV) with capacity volume of approximately 350 litters, in which multiple resources including electricity, communication, and moving image functions can be used. Within this space, installation of devices can be done by simple, prompt attachment by Velcro and pins with high degree of flexibility. Second, there is Small Experiment Area(SEA), with capacity volume of approximately 70 litters, in which electricity, communication, and moving image functions can also be used in the same way as WV. These spaces protect experiment devices and specimens from contingent loads by the crewmembers. Third, there is Work Bench with area of 0.5 square meters, on which can be used for maintenance, inspection and data operations of installed devices, etc. This bench can be stored in the rack during contingency. Chamber for Combustion Experiment(CCE) that is planned to be installed in WV is a pressure-resistant experimental container that can be used to seal hazardous materials from combustion experiments. This CCE has double sealing design in chamber itself, which resist gas leakage under normal the temperature and pressure. Electricity, communication, moving image function can be used in the same way as WV. JAXA Phase 2 Safety Review Panel(SRP) has been held in April, 2010. For safety analysis of MSPR, hazards were identified based on Fault Tree Analysis methodology and then these hazards were classified into either eight ISS standard-type hazards or eight unique-type hazards that requires special controls based on ISS common safety assessment methodology. Safety evaluation results are reported in the Safety Assessment Report(SAR) 1). Regarding structural failure, unique hazards are especially evaluated considering not only the tolerance for launch load but also load by crewmembers or orbital loads. Regarding electrical shock, electricity design up to secondary power is evaluated in unique hazard from a view point of Electrical design suitable for high voltage(32VDC or more) circuit. Regarding rupture/leakage of pressure system, hazards of fuel supply line, waste line for combustion gas, and pressure system including CCE are evaluated. Also evaluation for contamination due to hazardous gas leakage from CCE is conducted. External propagation of fire from CCE is also evaluated. In this report, we will show the overview of the result of safety assessment and future plan toward critical design phase activity.

Development of LM10-MIRA LOX/LNG expander cycle demonstrator engine

NASA Astrophysics Data System (ADS)

Rudnykh, Mikhail; Carapellese, Stefano; Liuzzi, Daniele; Arione, Luigi; Caggiano, Giuseppe; Bellomi, Paolo; D'Aversa, Emanuela; Pellegrini, Rocco; Lobov, S. D.; Gurtovoy, A. A.; Rachuk, V. S.

2016-09-01

This article contains results of joint works by Konstruktorskoe Buro Khimavtomatiki (KBKhA, Russia) and AVIO Company (Italy) on creation of the LM10-MIRA liquid-propellant rocket demonstrator engine for the third stage of the upgraded "Vega" launcher.Scientific and research activities conducted by KBKhA and AVIO in 2007-2014 in the frame of the LYRA Program, funded by the Italian Space Agency, with ELV as Prime contractor, and under dedicated ASI-Roscosmos inter-agencies agreement, were aimed at development and testing of a 7.5 t thrust expander cycle demonstrator engine propelled by oxygen and liquid natural gas (further referred to as LNG).

Ribbon cutting opens new ELV offices

NASA Technical Reports Server (NTRS)

2000-01-01

Viewed from the side, orbiter Discovery, with its seven-member crew, touches down on the landing strip at Edwards Air Force Base, Calif., after an 11-day mission to the International Space Station. The orbiter's main landing gear touched down on EAFB runway 22 at 5 p.m. With the aid of its drag chute, Discovery came to a complete stop at 5:01 p.m. At the conclusion of mission STS-92, Discovery and crew had traveled about 5.3 million statute miles. Following vehicle safing and preliminary offloading efforts, workers will begin preparations for Discovery's transcontinental ferry flight back to KSC on the back of NASA's modified Boeing 747.

Remote Advanced Payload Test Rig (RAPTR) Portable Payload Test System for the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Calvert, John; Freas, George, II

2017-01-01

The RAPTR was developed to test ISS payloads for NASA. RAPTR is a simulation of the Command and Data Handling (C&DH) interfaces of the ISS (MIL-STD 1553B, Ethernet and TAXI) and is designed to facilitate rapid testing and deployment of payload experiments to the ISS. The ISS Program's goal is to reduce the amount of time it takes a payload developer to build, test and fly a payload, including payload software. The RAPTR meets this need with its user oriented, visually rich interface. Additionally, the Analog and Discrete (A&D) signals of the following payload types may be tested with RAPTR: (1) EXPRESS Sub Rack Payloads; (2) ELC payloads; (3) External Columbus payloads; (4) External Japanese Experiment Module (JEM) payloads. The automated payload configuration setup and payload data inspection infrastructure is found nowhere else in ISS payload test systems. Testing can be done with minimal human intervention and setup, as the RAPTR automatically monitors parameters in the data headers that are sent to, and come from the experiment under test.

Earth Viewing Applications Laboratory (EVAL). Dedicated payload, standard test rack payload, sensor modifications

NASA Technical Reports Server (NTRS)

1976-01-01

The preliminary analysis of strawman earth-viewing shuttle sortie payloads begun with the partial spacelab payload was analyzed. The payloads analyzed represent the two extremes of shuttle sortie application payloads: a full shuttle sortie payload dedicated to earth-viewing applications, and a small structure payload which can fly on a space available basis with another primary shuttle payload such as a free flying satellite. The intent of the dedicated mission analysis was to configure an ambitious, but feasible, payload; which, while rich in scientific return, would also stress the system and reveal any deficiences or problem areas in mission planning, support equipment, and operations. Conversely, the intent of the small structure payload was to demonstrate the ease with which a small, simple, flexible payload can be accommodated on shuttle flights.

Space-Based Range

NASA Technical Reports Server (NTRS)

2008-01-01

Space-Based Range (SBR), previously known as Space-Based Telemetry and Range Safety (STARS), is a multicenter NASA proof-of-concept project to determine if space-based communications using NASA's Tracking and Data Relay Satellite System (TDRSS) can support the Range Safety functions of acquiring tracking data and generating flight termination signals, while also providing broadband Range User data such as voice, video, and vehicle/payload data. There was a successful test of the Range Safety system at Wallops Flight Facility (WFF) on December 20, 2005, on a two-stage Terrier-Orion spin-stabilized sounding rocket. SBR transmitted GPS tracking data and maintained links with two TDRSS satellites simultaneously during the 10-min flight. The payload section deployed a parachute, landed in the Atlantic Ocean about 90 miles downrange from the launch site, and was successfully recovered. During the Terrier-Orion tests flights, more than 99 percent of all forward commands and more than 95 percent of all return frames were successfully received and processed. The time latency necessary for a command to travel from WFF over landlines to White Sands Complex and then to the vehicle via TDRSS, be processed onboard, and then be sent back to WFF was between 1.0 s and 1.1 s. The forward-link margins for TDRS-10 (TDRS East [TDE]) were 11 dB to 12 dB plus or minus 2 dB, and for TDRS-4 (TDRS Spare [TDS]) were 9 dB to 10 dB plus or minus 1.5 dB. The return-link margins for both TDE and TDS were 6 dB to 8 dB plus or minus 3 dB. There were 11 flights on an F-15B at Dryden Flight Research Center (DFRC) between November 2006 and February 2007. The Range User system tested a 184-element TDRSS Ku-band (15 GHz) phased-array antenna with data rates of 5 Mbps and 10 Mbps. This data was a combination of black-and-white cockpit video, Range Safety tracking and transceiver data, and aircraft and antenna controller data streams. IP data formatting was used.

FLPP NGL Structural Subsystems Activity

NASA Astrophysics Data System (ADS)

Jaredson, D.; Ramusat, G.; Appel, S.; Cardone, T.; Persson, J.; Baiocco, P.; Lavelle, F.; Bouilly, Th.

2012-07-01

The ESA Future Launchers Preparatory Programme (FLPP) is the basis for new paradigms, investigating the key elements, logic and roadmaps to prepare the development of the safe, reliable and low cost next European Launch Vehicle (LV) for access to space (dubbed NGL - Next Generation LV), with an initial operational capability mid-next decade. In addition to carry cargo to conventional GTO or SSO, the European NGL has to be flexible enough to cope with new pioneering institutional missions as well as the evolving commercial payloads market. This achievement is broached studying three main areas relevant to ELVs: System concepts, Propulsion and Core Technology During the preliminary design activity, a number of design alternatives concerning NGL main structural subsystems have been investigated. Technology is one of the ways to meet the NGL challenges to either improve the performances or to reduce the cost or both. The relevant requirements allow to steer a ‘top-down’ approach for their conception and to propose the most effective technologies. Furthermore, all these technology developments represent a significant ‘bottom-up’ approach investment and concern a large range of activities. The structural subsystems portfolio of the FLPP ‘Core Technology’ activity encompasses major cutting-edge challenges for maturation of the various subsystems leading to reduce overall structural mass, increasing structural margins for robustness, metallic and composite containment of cryogenic propellants, significantly reducing fabrication and operations cost, etc. to derive performing upper and booster stages. Application of concurrent engineering methods will allow developments of performing technology demonstrators in terms of need, demonstration objective, size and cost yielding to safe, low-risk technical approaches for a future development. Potential ability of these advanced structural LV technologies to satisfy the system requirements of the NGL and their current and targeted technology readiness (i.e. TRL 6 by 2016) are being assessed to check whether a future flawless development could be performed within a given budget and schedule. The paper outlines the various technology developments for the pressurised and unpressurised structure subsystems and describes the implementation methodology, some of the current technology works performed and achieved accomplishments up to now. This is in strong connection with the “system” activity dealing with the same matter [1].

The LEAN Payload Integration Process

NASA Technical Reports Server (NTRS)

Jordan, Lee P.; Young, Yancy; Rice, Amanda

2011-01-01

It is recognized that payload development and integration with the International Space Station (ISS) can be complex. This streamlined integration approach is a first step toward simplifying payload integration; making it easier to fly payloads on ISS, thereby increasing feasibility and interest for more research and commercial organizations to sponsor ISS payloads and take advantage of the ISS as a National Laboratory asset. The streamlined integration approach was addressed from the perspective of highly likely initial payload types to evolve from the National Lab Pathfinder program. Payloads to be accommodated by the Expedite the Processing of Experiments for Space Station (EXPRESS) Racks and Microgravity Sciences Glovebox (MSG) pressurized facilities have been addressed. It is hoped that the streamlined principles applied to these types of payloads will be analyzed and implemented in the future for other host facilities as well as unpressurized payloads to be accommodated by the EXPRESS Logistics Carrier (ELC). Further, a payload does not have to be classified as a National Lab payload in order to be processed according to the lean payload integration process; any payload that meets certain criteria can follow the lean payload integration process.

Space nuclear power applied to electric propulsion

NASA Technical Reports Server (NTRS)

Vicente, F. A.; Karras, T.; Darooka, D.; Isenberg, L.

1989-01-01

Space reactor power systems with characteristics ideal for advanced spacecraft systems applications are discussed. These characteristics are: high power-to-weight ratio (15 to 33 W/kg); high volume density (high ballistic coefficient); no preferential orientation in orbit; long operational life; high reliability; and total launch and operational safety. These characteristics allow the use of electric propulsion to raise spacecraft from low earth parking orbits to operational orbits, greatly increasing the useful orbit payload for a given launch vehicle by eliminating the need for a separation injection stage. A proposed demonstration mission is described.

Space nuclear power system and the design of the nuclear electric propulsion OTV

NASA Technical Reports Server (NTRS)

Buden, D.; Garrison, P. W.

1984-01-01

Payload increases of three to five times that of the Shuttle/Centaur can be achieved using nuclear electric propulsion. Various nuclear power plant options being pursued by the SP-100 Program are described. These concepts can grow from 100 kWe to 1 MWe output. Spacecraft design aspects are addressed, including thermal interactions, plume interactions, and radiation fluences. A baseline configuration is described accounting for these issues. Safety aspects of starting the OTV transfer from an altitude of 300 km indicate no significant additional risk to the biosphere.

Effect of a dual-purpose cask payload increment of spent fuel assemblies from VVER 1000 Bushehr Nuclear Power Plant on basket criticality.

PubMed

Rezaeian, M; Kamali, J

2017-01-01

Dual-purpose casks can be utilized for dry interim storage and transportation of the highly radioactive spent fuel assemblies (SFAs) of Bushehr Nuclear Power Plant (NPP). Criticality safety analysis was carried out using the MCNP code for the cask containing 12, 18, or 19 SFAs. The basket materials of borated stainless steel and Boral (Al-B 4 C) were investigated, and the minimum required receptacle pitch of the basket was determined. Copyright © 2016 Elsevier Ltd. All rights reserved.

Spacelab Level 4 Programmatic Implementation Assessment Study. Volume 1: Representative payload definition

NASA Technical Reports Server (NTRS)

1978-01-01

Four types of Spacelab payloads were analyzed; these were considered to be representative of the Spacelab traffic model. The payloads were: (1) space processing - a single pallet payload; (2) combined astronomy - a five pallet payload; (3) life sciences - a long module payload; and (4) advanced technology lab - a short module plus train payload.

MINOTAUR (Maryland's innovative orbital technologically advanced University rocket)

NASA Technical Reports Server (NTRS)

Lewis, Mark J.; Akin, Dave; Lind, Charles; Rice, T. (Editor); Vincent, W. (Editor)

1992-01-01

Over the past decade, there has been an increasing interest in designing small commercial launch vehicles. Some of these designs include OSC's Pegasus, and AMROC's Aquila. Even though these vehicles are very different in their overall design characteristics, they all share a common thread of being expensive to design and manufacture. Each of these vehicles has an estimated production and operations cost of over $15000/kg of payload. In response to this high cost factor, the University of Maryland is developing a cost-effective alternative launch vehicle, Maryland's Innovative Orbital Technologically Advanced University Rocket (MINOTAUR). A preliminary cost analysis projects that MINOTAUR will cost under $10000/kg of payload. MINOTAUR will also serve as an enriching project devoted to an entirely student-designed-and-developed launch vehicle. This preliminary design of MINOTAUR was developed entirely by undergraduates in the University of Maryland's Space Vehicle Design class. At the start of the project, certain requirements and priorities were established as a basis from which to begin the design phase: (1) carry a 100 kg payload into a 200 km circular orbit; (2) provide maximum student involvement in the design, manufacturing, and launch phases of the project; and (3) use hybrid propulsion throughout. The following is the list of the project's design priorities (from highest to lowest): (1) safety, (2) cost, (3) minimum development time, (4) maximum use of the off-the-shelf components, (5) performance, and (6) minimum use of pyrotechnics.

STS-99 crew practice driving an M-113 during TCDT

NASA Technical Reports Server (NTRS)

2000-01-01

STS-99 Mission Specialist Mamoru Mohri, who is with the National Space Development Agency (NASDA) of Japan, practices driving an armored personnel carrier under the watchful eye of Capt. George Hoggard (riding on the front), trainer with the KSC Fire Department. The vehicle is part of emergency egress training during Terminal Countdown Demonstration Test (TCDT) activities and could be used by the crew in the event of an emergency at the pad during which the crew must make a quick exit from the area. Riding in the rear of the carrier are Mission Specialists Gerhard Thiele (center), Janice Voss (Ph.D.), and Commander Kevin Kregel. TCDT provides the crew with simulated countdown exercises, emergency egress training, and opportunities to inspect the mission payloads in the orbiter's payload bay. STS-99 is the Shuttle Radar Topography Mission, which will chart a new course, using two antennae and a 200-foot-long section of space station- derived mast protruding from the payload bay to produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Besides contributing to the production of better maps, these measurements could lead to improved water drainage modeling, more realistic flight simulators, better locations for cell phone towers, and enhanced navigation safety. Launch of Endeavour on the 11-day mission is scheduled for Jan. 31 at 12:47 p.m. EST.

Shuttle payload interface verification equipment study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1976-01-01

A preliminary design analysis of a stand alone payload integration device (IVE) is provided that is capable of verifying payload compatibility in form, fit and function with the shuttle orbiter prior to on-line payload/orbiter operations. The IVE is a high fidelity replica of the orbiter payload accommodations capable of supporting payload functional checkout and mission simulation. A top level payload integration analysis developed detailed functional flow block diagrams of the payload integration process for the broad spectrum of P/L's and identified degree of orbiter data required by the payload user and potential applications of the IVE.

Integrating International Space Station payload operations

NASA Technical Reports Server (NTRS)

Noneman, Steven R.

1996-01-01

The payload operations support for the International Space Station (ISS) payload is reported on, describing payload activity planning, payload operations control, payload data management and overall operations integration. The operations concept employed is based on the distribution of the payload operations responsibility between the researchers and ISS partners. The long duration nature of the ISS mission dictates the geographical distribution of the payload operations activities between the different national centers. The coordination and integration of these operations will be assured by NASA's Payload Operations Integration Center (POIC). The prime objective of the POIC is the achievement of unified operations through communication and collaboration.

Systems cost/performance analysis (study 2.3). Volume 2: Systems cost/performance model. [unmanned automated payload programs and program planning

NASA Technical Reports Server (NTRS)

Campbell, B. H.

1974-01-01

A methodology which was developed for balanced designing of spacecraft subsystems and interrelates cost, performance, safety, and schedule considerations was refined. The methodology consists of a two-step process: the first step is one of selecting all hardware designs which satisfy the given performance and safety requirements, the second step is one of estimating the cost and schedule required to design, build, and operate each spacecraft design. Using this methodology to develop a systems cost/performance model allows the user of such a model to establish specific designs and the related costs and schedule. The user is able to determine the sensitivity of design, costs, and schedules to changes in requirements. The resulting systems cost performance model is described and implemented as a digital computer program.

Selection of shuttle payload data processing drivers for the data system new technology study

NASA Technical Reports Server (NTRS)

1976-01-01

An investigation of all payloads in the IBM disciplines and the selection of driver payloads within each discipline are described. The driver payloads were selected on the basis of their data processing requirements. These requirements are measured by a weighting scheme. The total requirements for each discipline are estimated by use of the technology payload model. The driver selection process which was both a payload by payload comparison and a comparison of expected groupings of payloads was examined.

Control system and method for payload control in mobile platform cranes

DOEpatents

Robinett, III, Rush D.; Groom, Kenneth N.; Feddema, John T.; Parker, Gordon G.

2002-01-01

A crane control system and method provides a way to generate crane commands responsive to a desired payload motion to achieve substantially pendulation-free actual payload motion. The control system and method apply a motion compensator to maintain a payload in a defined payload configuration relative to an inertial coordinate frame. The control system and method can further comprise a pendulation damper controller to reduce an amount of pendulation between a sensed payload configuration and the defined payload configuration. The control system and method can further comprise a command shaping filter to filter out a residual payload pendulation frequency from the desired payload motion.

Collision avoidance sensor skin

NASA Technical Reports Server (NTRS)

1991-01-01

The objective was to totally eliminate the possibility of a robot (or any mechanism for that matter) inducing a collision in space operations. We were particularly concerned that human beings were safe under all circumstances. This was apparently accomplished, and it is shown that GSFC has a system that is ready for space qualification and flight. However, it soon became apparent that much more could be accomplished with this technology. Payloads could be made invulnerable to collision avoidance and the blind spots behind them eliminated. This could be accomplished by a simple, non-imaging set of 'Capaciflector' sensors on each payload. It also is evident that this system could be used to align and dock the system with a wide margin of safety. Throughout, lighting problems could be ignored, and unexpected events and modeling errors taken in stride. At the same time, computational requirements would be reduced. This can be done in a simple, rugged, reliable manner that will not disturb the form factor of space systems. It will be practical for space applications. The lab experiments indicate we are well on the way to accomplishing this. Still, the research trail goes deeper. It now appears that the sensors can be extended to end effectors to provide precontact information and make robot docking (or any docking connection) very smooth, with minimal loads impacted back into the mating structures. This type of ability would be a major step forward in basic control techniques in space. There are, however, baseline and restructuring issues to be tackled. The payloads must get power and signals to them from the robot or from the astronaut servicing tool. This requires a standard electromechanical interface. Any of several could be used. The GSFC prototype shown in this presentation is a good one. Sensors with their attendant electronics must be added to the payloads, end effectors, and robot arms and integrated into the system.

Acoustically-Responsive Scaffolds: Control of Growth Factor Release for Tissue Regeneration Using Ultrasound

NASA Astrophysics Data System (ADS)

Moncion, Alexander

Administration of exogenous growth factors (GFs) is a proposed method of stimulating tissue regeneration. Conventional administration routes, such as at-site or systemic injections, have yielded problems with efficacy and/or safety, thus hindering the translation of GF-based regenerative techniques. Hydrogel scaffolds are commonly used as biocompatible delivery vehicles for GFs. Yet hydrogels do not afford spatial or temporal control of GF release - two critical parameters for tissue regeneration. Controlled delivery of GFs is critical for angiogenesis, which is a crucial process in tissue engineering that provides oxygen and nutrients to cells within an implanted hydrogel scaffold. Angiogenesis requires multiple GFs that are presented with distinct spatial and temporal profiles. Thus, controlled release of GFs with spatiotemporal modulation would significantly improve tissue regeneration by recapitulating endogenous GF presentation. In order to achieve this goal, we have developed acoustically-responsive scaffolds (ARSs), which are fibrin hydrogels doped with sonosensitive perfluorocarbon (PFC) emulsions capable of encapsulating various payloads. Focused, mega-Hertz range, ultrasound (US) can modulate the release of a payload non-invasively and in an on-demand manner from ARSs via physical mechanisms termed acoustic droplet vaporization (ADV) and inertial cavitation (IC). This work presents the relationship between the ADV/IC thresholds and various US and hydrogel parameters. These physical mechanisms were used for the controlled release of fluorescent dextran in vitro and in vivo to determine the ARS and US parameters that yielded optimal payload release. The optimal ARS and US parameters were used to demonstrate the controlled release of basic fibroblast growth factor from an in vivo subcutaneous implant model - leading to enhanced angiogenesis and perfusion. Additionally, different acoustic parameters and PFCs were tested and optimized to demonstrate the controlled release of two encapsulated payloads within an ARS. Overall, ARSs are a promising platform for GF delivery in tissue regeneration applications.

STS-61 mission director's post-mission report

NASA Technical Reports Server (NTRS)

Newman, Ronald L.

1995-01-01

To ensure the success of the complex Hubble Space Telescope servicing mission, STS-61, NASA established a number of independent review groups to assess management, design, planning, and preparation for the mission. One of the resulting recommendations for mission success was that an overall Mission Director be appointed to coordinate management activities of the Space Shuttle and Hubble programs and to consolidate results of the team reviews and expedite responses to recommendations. This report presents pre-mission events important to the experience base of mission management, with related Mission Director's recommendations following the event(s) to which they apply. All Mission Director's recommendations are presented collectively in an appendix. Other appendixes contain recommendations from the various review groups, including Payload Officers, the JSC Extravehicular Activity (EVA) Section, JSC EVA Management Office, JSC Crew and Thermal Systems Division, and the STS-61 crew itself. This report also lists mission events in chronological order and includes as an appendix a post-mission summary by the lead Payload Deployment and Retrieval System Officer. Recommendations range from those pertaining to specific component use or operating techniques to those for improved management, review, planning, and safety procedures.

Analysis of Waves in Space Plasma (WISP) near field simulation and experiment

NASA Technical Reports Server (NTRS)

Richie, James E.

1992-01-01

The WISP payload scheduler for a 1995 space transportation system (shuttle flight) will include a large power transmitter on board at a wide range of frequencies. The levels of electromagnetic interference/electromagnetic compatibility (EMI/EMC) must be addressed to insure the safety of the shuttle crew. This report is concerned with the simulation and experimental verification of EMI/EMC for the WISP payload in the shuttle cargo bay. The simulations have been carried out using the method of moments for both thin wires and patches to stimulate closed solids. Data obtained from simulation is compared with experimental results. An investigation of the accuracy of the modeling approach is also included. The report begins with a description of the WISP experiment. A description of the model used to simulate the cargo bay follows. The results of the simulation are compared to experimental data on the input impedance of the WISP antenna with the cargo bay present. A discussion of the methods used to verify the accuracy of the model is shown to illustrate appropriate methods for obtaining this information. Finally, suggestions for future work are provided.

Fast Time Response Electromagnetic Particle Injection System for Disruption Mitigation

NASA Astrophysics Data System (ADS)

Raman, Roger; Lay, W.-S.; Jarboe, T. R.; Menard, J. E.; Ono, M.

2017-10-01

Predicting and controlling disruptions is an urgent issue for ITER. In this proposed method, a radiative payload consisting of micro spheres of Be, BN, B, or other acceptable low-Z materials would be injected inside the q =2 surface for thermal and runaway electron mitigation. The radiative payload would be accelerated to the required velocities (0.2 to >1km/s) in an Electromagnetic Particle Injector (EPI). An important advantage of the EPI system is that it could be positioned very close to the reactor vessel. This has the added benefit that the external field near a high-field tokamak dramatically improves the injector performance, while simultaneously reducing the system response time. A NSTX-U / DIII-D scale system has been tested off-line to verify the critical parameters - the projected system response time and attainable velocities. Both are consistent with the model calculations, giving confidence that an ITER-scale system could be built to ensure safety of the ITER device. This work is supported by U.S. DOE Contracts: DE-AC02-09CH11466, DE-FG02-99ER54519 AM08, and DE-SC0006757.

The DSI small satellite launcher

NASA Technical Reports Server (NTRS)

Nichols, S.; Gibbons, D.; Wise, J.; Nguyen, D.

1992-01-01

A new launcher has been developed by DSI, that is compatible with the GAS canisters. It has the proven capability to deploy a satellite from an orbiting Shuttle that is 18 inches in diameter, 31 inches long, and weighing 190 pounds. These DSI Launchers were used aboard the Discovery (STS-39) in May 1991 as part of the Infrared Background Signature Survey (IBSS) to deploy three small satellites known as Chemical Release Observation (CRO) satellites A, B, and C. Because the satellites contained hazardous liquids (MMH, UDMH, and MON-10) and were launched from GAS Cylinders without motorized doors, the launchers were required to pass NASA Shuttle Payload safety and verification requirements. Some of the more interesting components of the design were the V-band retention and separation mechanism, the separation springs, and the launcher electronics which provided a properly inhibited release sequence operated through the Small Payload Accommodations Switch Panel (SPASP) on board the Orbiter. The original plan for this launcher was to use a motorized door. The launcher electronics, therefore has the capability to be modified to accommodate the door, if desired.

14 CFR 415.59 - Information requirements for payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Information requirements for payload review... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.59 Information requirements for payload review. (a) A person requesting review of a particular payload or payload...

14 CFR 431.7 - Payload and payload reentry determinations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload and payload reentry determinations. 431.7 Section 431.7 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... payload reentry determination is required to reenter a payload to Earth on an RLV unless the proposed...

Kinematic optimization of upgrade to the Hobby-Eberly Telescope through novel use of commercially available three-dimensional CAD package

NASA Astrophysics Data System (ADS)

Wedeking, Gregory A.; Zierer, Joseph J.; Jackson, John R.

2010-07-01

The University of Texas, Center for Electromechanics (UT-CEM) is making a major upgrade to the robotic tracking system on the Hobby Eberly Telescope (HET) as part of theWide Field Upgrade (WFU). The upgrade focuses on a seven-fold increase in payload and necessitated a complete redesign of all tracker supporting structure and motion control systems, including the tracker bridge, ten drive systems, carriage frames, a hexapod, and many other subsystems. The cost and sensitivity of the scientific payload, coupled with the tracker system mass increase, necessitated major upgrades to personnel and hardware safety systems. To optimize kinematic design of the entire tracker, UT-CEM developed novel uses of constraints and drivers to interface with a commercially available CAD package (SolidWorks). For example, to optimize volume usage and minimize obscuration, the CAD software was exercised to accurately determine tracker/hexapod operational space needed to meet science requirements. To verify hexapod controller models, actuator travel requirements were graphically measured and compared to well defined equations of motion for Stewart platforms. To ensure critical hardware safety during various failure modes, UT-CEM engineers developed Visual Basic drivers to interface with the CAD software and quickly tabulate distance measurements between critical pieces of optical hardware and adjacent components for thousands of possible hexapod configurations. These advances and techniques, applicable to any challenging robotic system design, are documented and describe new ways to use commercially available software tools to more clearly define hardware requirements and help insure safe operation.

14 CFR 415.57 - Payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload review. 415.57 Section 415.57... TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.57 Payload review. (a) Timing. A payload review may be conducted as part of a license application review or may be requested by a payload...

Payload analysis for space shuttle applications (study 2.2). Volume 3: Payload system operations analysis (task 2.2.1). [payload system operations analysis for shuttles and space tugs

NASA Technical Reports Server (NTRS)

1972-01-01

The technical and cost analysis that was performed for the payload system operations analysis is presented. The technical analysis consists of the operations for the payload/shuttle and payload/tug, and the spacecraft analysis which includes sortie, automated, and large observatory type payloads. The cost analysis includes the costing tradeoffs of the various payload design concepts and traffic models. The overall objectives of this effort were to identify payload design and operational concepts for the shuttle which will result in low cost design, and to examine the low cost design concepts to identify applicable design guidelines. The operations analysis examined several past and current NASA and DoD satellite programs to establish a shuttle operations model. From this model the analysis examined the payload/shuttle flow and determined facility concepts necessary for effective payload/shuttle ground operations. The study of the payload/tug operations was an examination of the various flight timelines for missions requiring the tug.

Express Payload Project - A new method for rapid access to Space Station Freedom

NASA Technical Reports Server (NTRS)

Uhran, Mark L.; Timm, Marc G.

1993-01-01

The deployment and permanent operation of Space Station Freedom will enable researchers to enter a new era in the 21st century, in which continuous on-orbit experimentation and observation become routine. In support of this objective, the Space Station Freedom Program Office has initiated the Express Payload Project. The fundamental project goal is to reduce the marginal cost associated with small payload development, integration, and operation. This is to be accomplished by developing small payload accommodations hardware and a new streamlined small payload integration process. Standardization of small payload interfaces, certification of small payload containers, and increased payload developer responsibility for mission success are key aspects of the Express Payload Project. As the project progresses, the principles will be applied to both pressurized payloads flown inside the station laboratories and unpressurized payloads attached to the station external structures. The increased access to space afforded by Space Station Freedom and the Express Payload Project has the potential to significantly expand the scope, magnitude, and success of future research in the microgravity environment.

Satellite situation report, volume 33, number 4

NASA Technical Reports Server (NTRS)

1993-01-01

The Satellite Situation Report is a listing of those satellites (objects) currently in orbit and those which have previously orbited the Earth. Some objects are too small or too far from the Earth's surface to be detected; therefore, the Satellite Situation Report does not include all manmade objects orbiting the Earth. Generally, satellites are classified as follows: (1) Payloads may contain one or more functioning or nonfunctioning experiments. Usually only the owners of the satellites know if the experiments are functioning, and there is no one source which indicates the operational status of all payloads and/or experiments. Payloads are normally the first listed in the Satellite Situation Report, i.e., 1982 087A, unless there are multiple payloads for the launch. In which case, the first objects cataloged are usually all payloads, unless a subsequent payload is later identified after objects other than payloads have been cataloged. (2) Platforms are used to support a payload while it is being placed into orbit. A platform may remain in orbit long after its purpose is served, usually longer than rocket bodies. It is usually the first object identified in the Satellite Situation Report listing after the payload(s), i.e., 1982 087B (when a platform is not used, the first object after the payload(s) is usually the rocket body). (3) Rocket bodies are used to place the payload and platform (if one is used) into orbit. Some launches may have more than one rocket body because of the payload weight or the type of orbit or experiment. Most rocket bodies decay within a short time after the payload (and platform) have achieved orbit. Rocket bodies are usually the third object listed in the Satellite Situation Report after the payload(s), i.e., 1982 087C. (4) Debris in orbit occurs when parts (nose cone shrouds, lens or hatch covers) are separated from the payload, when rocket bodies or payloads disintegrate or explode, or when objects are placed into free space from manned orbiting spacecraft during operations. Debris is detected by its size and distance from the Earth. Debris objects are the last objects after payload(s), platform, and rocket body(s) listed in the Satellite Situation Report, i.e., 1982 087D, 1982 087E, 1982 087F.

1st Stage Separation Aerodynamics Of VEGA Launcher

NASA Astrophysics Data System (ADS)

Genito, M.; Paglia, F.; Mogavero, A.; Barbagallo, D.

2011-05-01

VEGA is an European launch vehicle under development by the Prime Contractor ELV S.p.A. in the frame of an ESA contract. It is constituted by four stages, dedicated to the scientific/commercial market of small satellites (300 ÷ 2500 kg) into Low Earth Orbits, with inclinations ranging from 5.2° up to Sun Synchronous Orbits and with altitude ranging from 300 to 1500 km. Aim of this paper is to present a study of flow field due to retro-rockets impingement during the 1st stage VEGA separation phase. In particular the main goal of the present work is to present the aerodynamic activities performed for the justification of the separation phase.

Atmospheric Propagation Analysis Program

DTIC Science & Technology

1993-01-01

1 0 9060’ Ors MI ot9 SWt We1M’ LSol ISo I 97 Delta T Temp Deg Fahrenheit Delta T Temp Deg Fahrenheit Date System Time Large 4-Bar Tank Grad Targ Grad...SS firt 0 SIX 1299 IC Ie IOO are Lce’tItor i"W ELVE ~99L’s P969 wz-s U&I _ _ _ _ _ _ _ _ _ _ _ _ _ _ 131__ _ _ _ _ _ _ _ _ _ L t Wi ISO IM M’s0 Vev...2. 4.6 1008. 02/ 27002 :54 0.0 58.9 2. 10.1 1008. 02/2621:30 0.9 60.9 1. 9.2 1008. 02/2703:00 0.0 57.3 1. 12 1002. 0222:5 .6. . . 00.0/20:4 0159.2 3. 91

KSC-08pd3323

NASA Image and Video Library

2008-10-22

CAPE CANAVERAL, Fla. - In the Payload Changeout Room, or PCR, on Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers use the payload ground-handling mechanism to transfer space shuttle Endeavour's STS-126 mission payload from the payload canister. The payload is the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. The payload later will be installed in Endeavour's payload bay. Endeavour is targeted for launch on Nov. 14. Photo credit: NASA/Kim Shiflett

SRMS History, Evolution and Lessons Learned

NASA Technical Reports Server (NTRS)

Jorgensen, Glenn; Bains, Elizabeth

2011-01-01

Early in the development of the Space Shuttle, it became clear that NASA needed a method of deploying and retrieving payloads from the payload bay. The Shuttle Remote Manipulator System (SRMS) was developed to fill this need. The 50 foot long robotic arm is an anthropomorphic design consisting of three electromechanical joints, six degrees of freedom, and two boom segments. Its composite boom construction provided a light weight solution needed for space operations. Additionally, a method of capturing payloads with the arm was required and a unique End Effector was developed using an electromechanical snare mechanism. The SRMS is operated using a Displays and Controls Panel and hand controllers located within the aft crew compartment of the shuttle. Although the SRMS was originally conceived to deploy and retrieve payloads, its generic capabilities allowed it to perform many other functions not originally conceived of. Over the years it has been used for deploying and retrieving constrained and free flying payloads, maneuvering and supporting EVA astronauts, satellite repair, International Space Station construction, and as a viewing aid for on-orbit International Space Station operations. After the Columbia accident, a robotically compatible Orbiter Boom Sensor System (OBSS) was developed and used in conjunction with the SRMS to scan the Thermal Protection System (TPS) of the shuttle. These scans ensure there is not a breach of the TPS prior to shuttle re-entry. Ground operations and pre mission simulation, analysis and planning played a major role in the success of the SRMS program. A Systems Engineering Simulator (SES) was developed to provide a utility complimentary to open loop engineering simulations. This system provided a closed-loop real-time pilot-driven simulation giving visual feedback, display and control panel interaction, and integration with other vehicle systems, such as GN&C. It has been useful for many more applications than traditional training. Evolution of the simulations, guided by the Math Model Working Group, showed the utility of input from multiple modeling groups with a structured forum for discussion.There were many unique development challenges in the areas of hardware, software, certification, modeling and simulation. Over the years, upgrades and enhancements were implemented to increase the capability, performance and safety of the SRMS. The history and evolution of the SRMS program provided many lessons learned that can be used for future space robotic systems.

Integrated payload and mission planning, phase 3. Volume 1: Integrated payload and mission planning process evaluation

NASA Technical Reports Server (NTRS)

Sapp, T. P.; Davin, D. E.

1977-01-01

The integrated payload and mission planning process for STS payloads was defined, and discrete tasks which evaluate performance and support initial implementation of this process were conducted. The scope of activity was limited to NASA and NASA-related payload missions only. The integrated payload and mission planning process was defined in detail, including all related interfaces and scheduling requirements. Related to the payload mission planning process, a methodology for assessing early Spacelab mission manager assignment schedules was defined.

Payload Operations Support Team Tools

NASA Technical Reports Server (NTRS)

Askew, Bill; Barry, Matthew; Burrows, Gary; Casey, Mike; Charles, Joe; Downing, Nicholas; Jain, Monika; Leopold, Rebecca; Luty, Roger; McDill, David;

Modular Countermine Payload for Small Robots

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

Herman Herman; Doug Few; Roelof Versteeg

2010-04-01

Payloads for small robotic platforms have historically been designed and implemented as platform and task specific solutions. A consequence of this approach is that payloads cannot be deployed on different robotic platforms without substantial re-engineering efforts. To address this issue, we developed a modular countermine payload that is designed from the ground-up to be platform agnostic. The payload consists of the multi-mission payload controller unit (PCU) coupled with the configurable mission specific threat detection, navigation and marking payloads. The multi-mission PCU has all the common electronics to control and interface to all the payloads. It also contains the embedded processormore » that can be used to run the navigational and control software. The PCU has a very flexible robot interface which can be configured to interface to various robot platforms. The threat detection payload consists of a two axis sweeping arm and the detector. The navigation payload consists of several perception sensors that are used for terrain mapping, obstacle detection and navigation. Finally, the marking payload consists of a dual-color paint marking system. Through the multi-mission PCU, all these payloads are packaged in a platform agnostic way to allow deployment on multiple robotic platforms, including Talon and Packbot.« less

Modular countermine payload for small robots

NASA Astrophysics Data System (ADS)

Herman, Herman; Few, Doug; Versteeg, Roelof; Valois, Jean-Sebastien; McMahill, Jeff; Licitra, Michael; Henciak, Edward

2010-04-01

Payloads for small robotic platforms have historically been designed and implemented as platform and task specific solutions. A consequence of this approach is that payloads cannot be deployed on different robotic platforms without substantial re-engineering efforts. To address this issue, we developed a modular countermine payload that is designed from the ground-up to be platform agnostic. The payload consists of the multi-mission payload controller unit (PCU) coupled with the configurable mission specific threat detection, navigation and marking payloads. The multi-mission PCU has all the common electronics to control and interface to all the payloads. It also contains the embedded processor that can be used to run the navigational and control software. The PCU has a very flexible robot interface which can be configured to interface to various robot platforms. The threat detection payload consists of a two axis sweeping arm and the detector. The navigation payload consists of several perception sensors that are used for terrain mapping, obstacle detection and navigation. Finally, the marking payload consists of a dual-color paint marking system. Through the multimission PCU, all these payloads are packaged in a platform agnostic way to allow deployment on multiple robotic platforms, including Talon and Packbot.

Commercially Hosted Government Payloads: Lessons from Recent Programs

NASA Technical Reports Server (NTRS)

Andraschko, Mark A.; Antol, Jeffrey; Horan, Stephen; Neil, Doreen

2011-01-01

In a commercially hosted operational mode, a scientific instrument or operational device is attached to a spacecraft but operates independently from the spacecraft s primary mission. Despite the expected benefits of this arrangement, there are few examples of hosted payload programs actually being executed by government organizations. The lack of hosted payload programs is largely driven by programmatic challenges, both real and perceived, rather than by technical challenges. Partly for these reasons, NASA has not sponsored a hosted payload program, in spite of the benefits and visible community interest in doing so. In the interest of increasing the use of hosted payloads across the space community, this paper seeks to alleviate concerns about hosted payloads by identifying these programmatic challenges and presenting ways in which they can be avoided or mitigated. Despite the challenges, several recent hosted payload programs have been successfully completed or are currently in progress. This paper presents an assessment of these programs, with a focus on acquisition, costs, schedules, risks, and other programmatic aspects. The hosted payloads included in this study are the Federal Aviation Administration's Wide Area Augmentation System (WAAS) payloads, United States Coast Guard's Automatic Identification System (AIS) demonstration payload, Department of Defense's IP Router In Space (IRIS) demonstration payload, the United States Air Force's Commercially Hosted Infrared Payload (CHIRP), and the Australian Defence Force's Ultra High Frequency (UHF) payload. General descriptions of each of these programs are presented along with issues that have been encountered and lessons learned from those experiences. A set of recommended approaches for future hosted payload programs is presented, with a focus on addressing risks or potential problem areas through smart and flexible contracting up front. This set of lessons and recommendations is broadly applicable to future hosted payload programs, whether they are technology demonstrations, communications systems, or operational sensors. Additionally, we present a basic cost model for commercial access to space for hosted payloads as a function of payload mass

Payload isolation and stabilization by a Suspended Experiment Mount (SEM)

NASA Technical Reports Server (NTRS)

Bailey, Wayne L.; Desanctis, Carmine E.; Nicaise, Placide D.; Schultz, David N.

1992-01-01

Many Space Shuttle and Space Station payloads can benefit from isolation from crew or attitude control system disturbances. Preliminary studies have been performed for a Suspended Experiment Mount (SEM) system that will provide isolation from accelerations and stabilize the viewing direction of a payload. The concept consists of a flexible suspension system and payload-mounted control moment gyros. The suspension system, which is rigidly locked for ascent and descent, isolates the payload from high frequency disturbances. The control moment gyros stabilize the payload orientation. The SEM will be useful for payloads that require a lower-g environment than a manned vehicle can provide, such as materials processing, and for payloads that require stabilization of pointing direction, but not large angle slewing, such as nadir-viewing earth observation or solar viewing payloads.

EXPRESS Rack: The Extension of International Space Station Resources for Multi-Discipline Subrack Payloads

NASA Technical Reports Server (NTRS)

Sledd, Annette; Danford, Mike; Key, Brian

2002-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System was developed to provide Space Station accommodations for subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify data interfaces at the development site, Functional Checkout Units to allow payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes, and facilitate simpler ISS payload development. Whereas most ISS Payload facilities are designed to accommodate one specific type of science, the EXPRESS Rack is designed to accommodate multi-discipline research within the same rack allowing for the independent operation of each subrack payload. On-orbit operations began with the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support long-running payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Sustaining Engineering and Logistics and Maintenance functions are in place to maintain operations and to provide software upgrades.

The Extension of ISS Resources for Multi-Discipline Subrack Payloads

NASA Technical Reports Server (NTRS)

Sledd, Annette M.; Gilbert, Paul A. (Technical Monitor)

2002-01-01

The EXpedite the processing of Experiments to Space Station or EXPRESS Rack System was developed to provide Space Station accommodations for subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify data interfaces at the development site, Functional Checkout Units to allow payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes, and facilitate simpler ISS payload development. Whereas most ISS Payload facilities are designed to accommodate one specific type of science, the EXPRESS Rack is designed to accommodate multi-discipline research within the same rack allowing for the independent operation of each subrack payload. On-orbit operations began with the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support long-running payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Sustaining Engineering and Logistics and Maintenance functions are in place to maintain operations and to provide software upgrades.

Test and analysis procedures for updating math models of Space Shuttle payloads

NASA Technical Reports Server (NTRS)

Craig, Roy R., Jr.

1991-01-01

Over the next decade or more, the Space Shuttle will continue to be the primary transportation system for delivering payloads to Earth orbit. Although a number of payloads have already been successfully carried by the Space Shuttle in the payload bay of the Orbiter vehicle, there continues to be a need for evaluation of the procedures used for verifying and updating the math models of the payloads. The verified payload math models is combined with an Orbiter math model for the coupled-loads analysis, which is required before any payload can fly. Several test procedures were employed for obtaining data for use in verifying payload math models and for carrying out the updating of the payload math models. Research was directed at the evaluation of test/update procedures for use in the verification of Space Shuttle payload math models. The following research tasks are summarized: (1) a study of free-interface test procedures; (2) a literature survey and evaluation of model update procedures; and (3) the design and construction of a laboratory payload simulator.

Safety Considerations in the Ground Environment

NASA Technical Reports Server (NTRS)

Kirkpatrick, Paul D.; Palo, Thomas E.

2007-01-01

In the history of humankind, every great space adventure has begun on the ground. While this seems to be stating the obvious, mission and spacecraft designers who have overlooked this fact have paid a high price, either in loss or damage to the spacecraft pre-launch, or in mission failure or reduction. Spacecraft personnel may risk not only their flight hardware, but they may also risk their lives, their co-workers lives and even the general public by not heeding safety on the ground. Their eyes may be on the stars but their feet are on the ground! One additional comment: Although the design requirements are very different for human rated and nonhuman rated flight hardware, while on the ground that flight hardware (and its ground support equipment) doesn't care about what it is flying on. On the ground, additional requirements are often levied to protect the work force and general public. (Authors' Note: The source material for this chapter is primarily taken from the Kennedy Space Center Handbook (KHB) 1700.7/45 SW Handbook S-100 Space Shuttle Payload Ground Safety Handbook and the authors' personal experiences.

Design guide for low cost standardized payloads, volume 1

NASA Technical Reports Server (NTRS)

1972-01-01

Concept point designs of low cost and refurbishable spacecraft, subsystems, and modules revealed payload program savings up to 50 percent. The general relationship of payload approaches to program costs; cost reductions from low cost standardized payloads; cost effective application of payload reliability, MMD, repair, and refurbishment; and implementation of standardization for future spacecraft are discussed. Shuttle interfaces and support equipment for future payloads are also considered

Spectrum for UAS Control and Non-Payload Communications

NASA Technical Reports Server (NTRS)

Kerczewski, Robert J.

2013-01-01

There is an increasing need to fly UAS in the NAS to perform missions of vital importance to National Security and Defense, Emergency Management, and Science as well as commercial applications (e.g. cargo transport). To enable integration of UAS into the National Airspace System, several critical technical barriers must be eliminated, including: Separation Assurance/Sense and Avoid - the uncertainty surrounding the ability to interoperate in ATC environments and maintain safe separation from other aircraft in the absence of an on-board pilot. Human Systems Integration - lack of standards and guidelines with respect to UAS display information as well as lack of Ground Control Station (GCS) design requirements to operate in the NAS. Certification - lack of airworthiness requirements and safety-related data specific to the full range of UAS, or for their avionics systems or other components. Communications - lack of standard, certifiable data links and aviation safety spectrum to operate such links for civil UAS control communications.

Structural Design Requirements and Factors of Safety for Spaceflight Hardware: For Human Spaceflight. Revision A

NASA Technical Reports Server (NTRS)

Bernstein, Karen S.; Kujala, Rod; Fogt, Vince; Romine, Paul

2011-01-01

This document establishes the structural requirements for human-rated spaceflight hardware including launch vehicles, spacecraft and payloads. These requirements are applicable to Government Furnished Equipment activities as well as all related contractor, subcontractor and commercial efforts. These requirements are not imposed on systems other than human-rated spacecraft, such as ground test articles, but may be tailored for use in specific cases where it is prudent to do so such as for personnel safety or when assets are at risk. The requirements in this document are focused on design rather than verification. Implementation of the requirements is expected to be described in a Structural Verification Plan (SVP), which should describe the verification of each structural item for the applicable requirements. The SVP may also document unique verifications that meet or exceed these requirements with NASA Technical Authority approval.

Fabrication and Testing of Ceramic Matrix Composite Rocket Propulsion Components

NASA Technical Reports Server (NTRS)

Effinger, M. R.; Clinton, R. C., Jr.; Dennis, J.; Elam, S.; Genge, G.; Eckel, A.; Jaskowiak, M. H.; Kiser, J. D.; Lang, J.

2001-01-01

NASA has established goals for Second and Third Generation Reusable Launch Vehicles. Emphasis has been placed on significantly improving safety and decreasing the cost of transporting payloads to orbit. Ceramic matrix composites (CMC) components are being developed by NASA to enable significant increases in safety and engineer performance, while reducing costs. The development of the following CMC components are being pursued by NASA: (1) Simplex CMC Blisk; (2) Cooled CMC Nozzle Ramps; (3) Cooled CMC Thrust Chambers; and (4) CMC Gas Generator. These development efforts are application oriented, but have a strong underpinning of fundamental understanding of processing-microstructure-property relationships relative to structural analyses, nondestructive characterization, and material behavior analysis at the coupon and component and system operation levels. As each effort matures, emphasis will be placed on optimizing and demonstrating material/component durability, ideally using a combined Building Block Approach and Build and Bust Approach.

Analysis of nuclear waste disposal in space, phase 3. Volume 2: Technical report

NASA Technical Reports Server (NTRS)

Rice, E. E.; Miller, N. E.; Yates, K. R.; Martin, W. E.; Friedlander, A. L.

1980-01-01

The options, reference definitions and/or requirements currently envisioned for the total nuclear waste disposal in space mission are summarized. The waste form evaluation and selection process is documented along with the physical characteristics of the iron nickel-base cermet matrix chosen for disposal of commercial and defense wastes. Safety aspects of radioisotope thermal generators, the general purpose heat source, and the Lewis Research Center concept for space disposal are assessed as well as the on-pad catastrophic accident environments for the uprated space shuttle and the heavy lift launch vehicle. The radionuclides that contribute most to long-term risk of terrestrial disposal were determined and the effects of resuspension of fallout particles from an accidental release of waste material were studied. Health effects are considered. Payload breakup and rescue technology are discussed as well as expected requirements for licensing, supporting research and technology, and safety testing.